ГАЗОВЫЙ КАНАЛ ДЛЯ ГАЗОВОЙ ТУРБИНЫ И ГАЗОВАЯ ТУРБИНА, СОДЕРЖАЩАЯ ТАКОЙ ГАЗОВЫЙ КАНАЛ

Газовый канал для газовой турбины образован концентрическими внутренним и охватывающим его на расстоянии наружным корпусами. Внутренний корпус и наружный корпус взаимосвязаны посредством множества радиальных поддерживающих стоек. Внутренний корпус, наружный корпус и радиальные поддерживающие стойки снабжены термостойкой облицовкой для защиты от отработанных газов. Облицовки поддерживающих стоек, наружного корпуса и внутреннего корпуса разделены на множество отдельных сегментов, закрепленных на опорной конструкции с обеспечением свободного индивидуального термического расширения отдельных сегментов. Опорная конструкция содержит множество монтажных узлов в области наружного корпуса и внутреннего корпуса. Монтажные узлы закреплены на концентрической оболочке посредством радиальных стоек, причем монтажные узлы соответствующих сегментов закреплены винтами. Другое изобретение группы относится к газовой турбине включающей указанный выше газовый канал, по которому выходят отработанные газы. Группа ...

ГАЗОВАЯ ТУРБИНА, СОДЕРЖАЩАЯ КОРПУС КОМПРЕССОРА С ВПУСКНЫМ ОТВЕРСТИЕМ ДЛЯ ОХЛАЖДЕНИЯ КОРПУСА КОМПРЕССОРА, И ИСПОЛЬЗОВАНИЕ УКАЗАННОЙ ГАЗОВОЙ ТУРБИНЫ

Изобретение относится к энергетике. Газовая турбина, содержащая ротор в сборе и корпус компрессора. При этом корпус компрессора содержит внутреннюю камеру корпуса компрессора для размещения ротора в сборе и внешнюю камеру для охлаждения корпуса компрессора. Внутренняя камера корпуса компрессора и внешняя камера корпуса компрессора отделены друг от друга с помощью разделительной стенки корпуса, а внешняя камера корпуса компрессора содержит граничную стенку корпуса. Граничная стенка корпуса содержит впускное отверстие для подачи входящего потока охлаждающего газа с охлаждающим газом во внешнюю камеру корпуса компрессора для охлаждения корпуса компрессора таким образом, что градиенты температур материала в тангенциальном направлении в корпусе компрессора уменьшаются по сравнению с неохлаждаемым корпусом компрессора. Также представлен способ эксплуатации газовой турбины. Изобретение позволяет уменьшить вероятность возникновения механического повреждения газовой турбины, связанного с температурным ...

Устройство для соединения внутреннего и наружного корпусов турбомашины

Изобретение относится к области турбо- и авиадвигателестроения, а именно к устройствам соединения наружных и внутренних корпусов турбомашины. Устройство для соединения внутреннего и наружного корпусов 1 и 2 турбомашины содержит тяги 3, концы которых шарнирно соединены с соответствующими кронштейнами 5 корпуса 2 и кронштейнами 4 корпуса 1, а также промежуточный кольцевой элемент 9. Кронштейны 4 и 5 закреплены на соответствующих корпусах 1 и 2 посредством средства силового крепления. На внутренней поверхности корпуса 2, выполненного с фланцами горизонтального разъема 6, сформирован кольцевой паз, в котором установлен элемент 9, закрепленный с возможностью разъема на кронштейнах 5. При этом средства силового крепления со стороны корпуса 2 проходят насквозь через элемент 9 и образуют зазор с последним. Изобретение направлено на повышение удобства сборки, ускорение и упрощение процесса сборки при обеспечении требуемой взаимосвязи между внутренним и наружным корпусами в работе. 2 з.п. ф-лы, 3 ...

Улитка для выхлопных газов газотурбинного двигателя

Изобретение относится к конструкциям авиационных газотурбинных двигателей, в частности к конструкциям узлов для отвода горячих газов, и может быть применено в газоперекачивающих агрегатах - ГПА или энергетических установках на базе газотурбинного двигателя - ГТД. Задача создания изобретения: увеличение циклической прочности и ресурса улитки. Решение указанной задачи достигнуто в улитке для выхлопных газов газотурбинного двигателя, содержащей корпус с передней, задней и боковыми стенками, размещенный между передней и задней стенками корпуса осерадиальный диффузор, имеющий полость для размещения в ней выходного узла газотурбинного двигателя, а также содержащий внутреннюю и наружную обечайки с фланцами, при этом в улитке каждый из фланцев внутренней и наружной обечаек диффузора выполнен составным в виде кольца и кольцевой обечайки, соединенных между собой сваркой, кольцо фланца внутренней обечайки диффузора изготовлено из полой металлической трубы, а кольцо фланца наружной обечайки диффузора ...

ПАРОВАЯ ТУРБИНА

... 1. Паровая турбина (10), содержащая внешний корпус (12), внутренний кожух (14) внутри внешнего корпуса, включающий верхнюю и нижнюю диафрагмы (16, 18), присоединенные друг к другу вдоль горизонтальной соединительной средней линии, причем верхняя и нижняя диафрагмы имеют совмещающие фланцы (19, 21) на соединительной средней линии и углубления (40) во фланцах для совмещения друг с другом, и эластичное уплотнение (43), частично расположенное в каждом из совмещающих углублений, включающее уплотнительную основу (44), образованную из многочисленных слоев (46, 48, 50, 52) из различных материалов для эластичного уплотнения совмещающих фланцев верхней и нижней диафрагм друг с другом вдоль горизонтальной соединительной средней линии. 2. Паровая турбина по п.1, в которой материалы уплотнительной основы содержат плетеный металлический сердечник (46), волокно (48), металлическую фольгу (50) и защитный слой (52). 3. Паровая турбина по п.1, в которой материалы уплотнительной основы содержат внутренний ...

СПОСОБ ИЗГОТОВЛЕНИЯ КАРТЕРА СТАТОРА ТУРБИНЫ

... 1. Способ изготовления картера статора турбины, при этом картер содержит кожух (105), отличающийся тем, что между стенками частей (01, 02, 03, Е1, Е2) литейной формы, состоящей, по меньшей мере, из двух частей, предусматривают полость, имеющую форму, соответствующую форме упомянутого кожуха (105), жестко соединяют сердечники (10), выполненные из растворимого материала, по меньшей мере, с одной из частей (Е1) литейной формы, при этом сердечники удерживаются на определенном расстоянии от стенки упомянутой части и соответствуют свободным пространствам (110), которые необходимо оставить внутри кожуха (105), заполняют упомянутую полость порошком (24) металлического сплава, спекают порошок (24) горячим изостатическим прессованием, удаляют сердечники (10) путем растворения и извлекают отлитый таким образом кожух (105) из формы. 2. Способ по п.1, отличающийся тем, что размещают между сердечниками (10) вставки (20), соответствующие каналам (12) циркуляции между упомянутыми свободными пространствами ...

СИСТЕМА РЕГУЛИРОВАНИЯ ТЕМПЕРАТУРЫ ОТКЛЮЧЕНИЯ ТУРБИННОГО ДВИГАТЕЛЯ С ВСПРЫСКИВАЮЩИМ СОПЛОМ ДЛЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

ТУРБОНАГНЕТАТЕЛЬ

Двухпоточный цилиндр турбины

Изобретение относится к паротурбост- роению, может быть использовано в конструкциях двухпоточных цилиндров турбин и позволяет повысить экономичность и надежность . Двухпоточный цилиндр содержит корпус 1, в котором размещены двухпоточ- ная радиально-осевая ступень 2, осевые ступени 8 и камеры 9 отбора пара На покрывающих оболочках 7 рабочего колеса 6 выполнены дополнительные каналы 11, закрытые по всей ширине кольцевыми оболочками 10 и образующие параллельные центростремительные рабочие колеса 12, входящие как элементы в состав интегральной радиально-осевой ступени 15. На выходе из колес 12 над поверхностью 13 колеса 6 расположены изолированные от основного потока камеры 14 отбора пара оптимального давления. Пар после направляющих лопаток 4 поступает в колесо 6 и каналы 11 колес 12, в последних из которых пар расширяется автономно с установлением в камерах 14 отбора пара оптимального давления. Отбор пара из камер 14 не нарушает структуру основного потока пара, что повышает КПД и вибрационную ...

Фланцевое соединение для паровых цилиндров или паропроводов

Способ ремонта литых корпусов турбины

Цилиндр паровой турбины

I. ЦИЛИНДР ПАРОВОЙ ТУРБИН содержащий внутренний и наружный корпусы с фланцами горизонтального разъема, камеры между корпусами и между наружным корпусом и обоймами, при этом в нижней части камер установлен коллектор С запорно-регулирующей арматурой на входе и парораспределительными трубами с отверстиями , отличающийся тем, что, с целью повьоиения надежности и экономичности, цилиндр снабжен расположенным в верхней части камер дополнительным коллектором с запорнорегулирующей арматурой на входе и парораспределительными трубами с отверстиями, оба коллектора расположены вдоль цилиндра, а парораспределительные трубы установлены эквидистантно внутренней поверхности наружного корпуса. ю 05 О ND ч1 ...

Steam turbine housing inlet section e.g. for power station turbine

An inlet section of a turbine housing including a flange connection (4,5), having a number of though-flow openings (7) to a valve housing (2) for a control valve (3), in which the flange connection (4,5) has a sealing surface (15) enclosing each of the through-flow openings (7). The sealing surface (15) between adjacent through-flow apertures (7) specifically has a figure-of-eight or waisted outer contour.

Turbine machine such as axial and radial compressor

The turbine machine has a hot-running component made of high-alloy heat-resistant steel, supported by a frame or casing part, and connected to it so that the supporting and fixing elements of the hot-running component can expand in all three axial directions, so that the center point, adjusted in the cold state, remains where it is. Thermal insulation (37) is fitted in the contact region of the supporting and fixing elements (25-27) which act with each other. The insulation withstands the mechanical and thermal loads from the machine.

Hochtemperaturturbine

Zusammenbau eines Stators für eine rotierende Maschine.

Mantelringsegment eines Turbinentriebwerks und Aufhängevorrichtung

Gehaeuse fuer Dampf- oder Gasturbinen

Aufhängung eines Innengehäuses in einem äusseren Turbinengehäuse

Flüssigkeitskühlsystem eines durch einen Turbolader aufgeladenen Verbrennungsmotors und Verfahren zur Kühlung eines Turbinengehäuses eines Turboladers

Ein Flüssigkeitskühlsystem (16) eines durch einen Turbolader (1) aufgeladenen Verbrennungsmotors umfasst einen von einer Kühlmittelpumpe (34) betreibbaren ersten Kühlkreislauf (17), der durch einen Motorblockkühlmantel (18) verläuft, und einen von dem ersten Kühlkreislauf (17) abgezweigten zweiten Kühlkreislauf (21), der durch einen zwischen einer inneren Wand (9) und einer äußeren Wand (10) eines doppelwandigen Turbinengehäuses (15) des Turboladers (1) ausgebildeten Kühlmantel (8) verläuft.

Improvements in or relating to pump, compressor, turbine or the like assemblies

... 956,732. Centrifugal pumps; turbine casings. DE LAVAL STEAM TURBINE CO. April 17, 1962 [Aug. 11, 1961], No. 14920/62. Headings F1C and F1T. An assembly comprises a series of axially stacked sections constituting the stages of a pump, compressor, turbine or the like and a number of flat double-ended tie bars which extend parallel to the longitudinal axis of the assembly with their flat faces substantially tangential to an arc about the axis, the heads of the tie bars, being engaged respectively behind oppositely facing faces of the respective first and last section of the series for maintaining the assembled sections in axially-compressed stacked relationship. An outer casing 4, Fig. 1, of a pump 2 contains an inner assembly which comprises nested concentric sections 14 positioned between end sections 16, 18, and diffusers 22 bolted to the sections. The sections 14, 16, 18 are clamped together by flat oblong steel tie bars 24 provided with heads 26 having shoulders 28. As shown in Fig. 2 ...

Improvements in or relating to steam turbines

... 486,340. Elastic - fluid turbines. RODER, K. March 1, 1937, Nos. 6118, 6119, and 6120. Convention dates, Feb. 29, 1936, Oct. 9, 1936, and Nov. 4, 1936. [Class 110 (iii)] A steam turbine has a guide blade carrier a, which though subdivided in at least one axial plane, is formed as a true body of revolution, i.e. any section in a plane at right-angles to the axis of rotation of the rotor b is a true circle, and is held in position by one or more supporting members d, d<1>, lying in the steam space and themselves constituting true bodies of revolution, the carrier and the supporting member or members being so assembled that the subdivided carrier as a whole acts as an undivided true body of revolution. One of the supporting members d<2> may be constituted by a single unit, i.e. a ring or it may be subdivided in an axial plane at right-angles to the plane of subdivision of the carrier. One of the supporting members c<1> may also be carried by an internal annular wall c<11> integral and concentric ...

Improvements in or relating to elastic fluid turbines such as steam turbines

... 754,580. Elastic-fluid turbines. WESTINGHOUSE ELECTRIC INTERNATIONAL CO . May 14, 1954 [May 20, 1953], No. 14146/54. Class 110(3) An elastic-fluid turbine comprises inner and outer casings between which are longitudinal passages open to the low-pressure end of the turbine, working fluid inlets extending laterally through the casings adjacent the high-pressure end, and an exhaust outlet formed in the outer casing adjacent, the high-pressure end so that working fluid discharged from the turbine flower over the longitudinal extent of the inner casing for cooling purposes. Steam passes through two sets of inlet pipes 25, 26, 27 which extend through the outer casing 10 and inner casing 11 to two sets of nozzle boxes 33, 34, 35. After passing through impulse blading 13, the steam flows through passages 39 between the nozzle boxes to reaction blading 14, 14a and is exhausted through spaces 22 between the casings to an outlet 23. The steam cools adjacent hot parts as it flows through the passages ...

Axial flow turbines and compressors

... 757,278. Axial-flow turbines and compressors. SULZER FRERES SOC. ANON. Aug. 20, 1954 [Aug. 21, 1953], No. 24362/54. Classes 110(1) and 110 (3) In an axial-flow turbine or compressor, the rotor is supported at both ends and the fabricated welded casing is provided with a supporting structure which is substantially symmetrical with regard to the horizontal central plane and to the vertical longitudinal central plane and consists of several ribs distributed around the circumference of the casing and joined at the ends to two annular supporting bodies disposed coaxially with the rotor in the vicinity of the rotor bearings, the pressure-retaining part of the casing consisting of a sheet metal jacket welded to the supporting structure. In the gas turbine shown, the supporting structure for the sheet metal jacket 7 comprises longitudinal ribs 4 and the flanges 5, 6 which connect the upper and lower parts of the casing. Annular supporting members 9, 12 and 13, each divided in the central horizontal ...

Improvements in and relating to elastic fluid turbines

... 304,479. British Thomson-Houston Co., Ltd., and Collingham, R. H. Jan. 27, 1928. Casings. - In order to prevent "creeping " the casing of a turbine operating with elastic fluid at a very high temperature is made in two portions A, B, the portion B which is subjected to the very high temperature being under no tensile stress, but under compression stresses of negligible or low value only. This is achieved by circulating in the space between the casings A, B, fluid of the same pressure as, but of lower temperature than, that supplied by the nozzles N to the turbine in the casing B. The joint J, H between the casings is made tight, but a slight clearance is left in the joint C to allow heating fluid to leak away. The heating chamber is supplied through a connection E, and the turbine is separately supplied with superheating fluid to leak away. The heating from swivelling couplings G joined to supply pipes F. The internal casing B is lagged at O with non-conducting material.

Plates for clamping overlapping panels and bands

Panels 42 and bands 38 are joined together by overlapping to form a flowpath assembly in a gas turbine, by means of tripod plates 50 and fasteners 46. Each tripod plate 50 has a part-spherical seat 56 for receiving a washer 52, and a pair of projections 58 and a single leg 60 for respectively engaging the panel 42 and the band 38. Circumferential movement is permitted between the panels and bands while maintaining sealing. ...

Composite tubular woven seal for steam turbine diaphragm horizontal joint interfaces

Upper and lower diaphragms 16, 18 of a steam turbine have mating flanges 21 forming a horizontal midline joint interface. Each flange has a groove 40 which registers with a corresponding groove in the opposite flange. A composite woven tubular seal 43 is provided in the mating grooves. The seal comprises an inner woven metal core 46 surrounded by an annular silica fiber layer 48, in turn surrounded by a metal foil 50 with an outer protective covering of a braided stainless steel 52. Upon joining the diaphragms to one another, the compliant seal generally conforms to a maximum to the shape of the grooves, maintaining a seal between the diaphragms along the horizontal midline joint.

A spacer arrangement

Improvements relating to the construction of stator elements of turbines, compressors or like machines

... 597,165. Turbines; axial-flow compressors. POWER JETS (RESEARCH & DEVELOPMENT), Ltd., and McLEOD, R. C. Jan. 23, 1945, No. 1855. [Classes 110 (i) and 110 (iii)] In order to maintain the blade tip clearances during starting and changes of temperature, the rotor blade shrouding of a compressor or turbine is formed as an inner wall which has freedom for circumferent ial expansion located in a rigid outer casing so that it may expand without increasing its diameter. which is fixed by the outer casing. The rotor blade shrouding 27, Fig. 2 and 3, consists of a number of segments interconnected by strips 28 slidably located in slots in the segments. Clearance spaces 29 allow expansion in the peripheral direction. The segments are supported by steps 27a which engage the rear edges of inlet blade platforms 17 and flanges 32 provided with a lug which engage a peripheral groove in the outer casing 20. A cooling air space 30 is formed between the segments and the casing 20. Both the outer casing and ...

Mechanical system for a turbine engine, turbine engine, and method for attaching a mechanical system within a turbine engine

The invention relates to a mechanical system (100) for a turbine engine, including a turbine engine part to be attached, and a plurality of threaded attachment elements (310, 330) that are mounted onto the part, one after the other, along a line (250), wherein attachment elements are arranged so as to rotatably interlock by engaging with one another. Said self-locked elements (310, 330) engage in pairs (300), each pair (300) including two self-locking elements directly adjacent along the line (250). The distance between the thread axes (250) of the two self-locked elements of at least one of said pairs (300) is strictly less than the distance between either of said two thread axes and the axis of either of the two attachment elements that are arranged on the line (250) on either side of said pair (300).

Improvements in or relating to Steam Turbines.

... 105,933. Baumann, K. Feb. 4, 1916. Axial-flow type; casings; exhaust, disposing of; mounting and supporting.-R e l a t e s mainly to improved constructions of turbine exhaust casings for axial-flow turbines, said casings conducting the exhaust steam from the last row or rows of moving blades to the exhaust outlet or condenser, and the invention is particularly applicable to multiple exhaust turbines of the kind described in Specification 14053/15. In an ordinary axial-flow turbine, Figs. 1 and 2, the whole of the exhaust steam leaving the moving blades 8, according to the invention, is deflected outwards into a substantially radial direction by the casing wall 10 and then conducted by guide walls 11 in a number of segmental portions outwardly away from the turbine axis in a direction substantially transverse thereto. The exhaust outlet 6 is long and narrow, thus distributing the steam over the whole length of the condenser 7, which may be supported directly from the outlet 6, no expansion ...

Improvements in or relating to high-pressure axial-flow machines such as compressorsand turbines

... 990,543. Axial-flow compressors and turbines. ESCHER WYSS A.G. July 14, 1961 [July 20, 1960], No. 25643/61. Headings F1C and F1T. A high-pressure axial-flow machine comprises a welded sheet-metal housing of spherical form and a guide-blade carrier mounted within the housing and connected to the latter by an annular partition which divides the housing cavity into an inlet chamber and and outlet chamber. In the compressor shown, a spherical housing is split on a horizontal plane into two sheet-metal hemispheres 2, 3 and 4, 5 which are bolted together at flanges provided at the horizontal plane. A cylindrical guide blade carrier 11 is supported at its discharge end by means of a ring 14 welded to a conical partition 12, the latter being welded to a reinforcing ring 13 which is welded to the spherical portions 2, 3, 4, 5. The guide blade carrier 11 and the conical partition 14 are each in two halves, bolted together at flanges 29 or 30. At its inlet end, the guide blade carrier 11 is carried ...

Improvements in Radial Flow Steam Turbines.

... 110,786. Baumann, K. Oct. 28, 1916, Addition to 105,933. Radial-flow (bladed) type; exhaust, disposing of; mounting and supporting. -The exhaust casing described in the parent Specification is modified for use with radial-flow turbines, for example with the Ljungstr÷m type of turbine, by omitting the guides for deflecting the steam leaving the turbine outwardly into a radial direction of flow. The exhaust casing 7 has a number of internal guide walls 8 conducting segmental portions of steam leaving the blade ring 3 to the outlet 11, and is supported together with the condenser 14 on feet 12, 13.

Shroud assembly for a gas turbine engine

A shroud assembly is pneumatically operated to adjust the clearance between the shroud segments and the tips of the rotor blades of an associated rotor. The assembly comprises a casing to which is secured a wall member which defines a chamber whose pressure may be varied by a valve. The wall member carries shroud segments some of which define the static wall with which the rotor blades co-operate. In order to allow proper movement of the shroud segments the support means which carry the segments from the wall are arranged to be small in axial extent compared with that of the wall.

Compressor casings

A gas turbine engine is so constructed that the clearance or gap between the rotor and stator, especially at the outer diameter range of a radial flow end stage, is optimally maintained under all operating conditions. For this purpose the housing in the axial-flow/radial-flow compressor is constructed as a two shell housing. The outer housing shell is mounted as part of the engine structure, whereby the inner housing shell is exposed substantially only to forces or loads caused by compressor fluid flow. The material of the outer housing shell has a heat expansion coefficient in the axial direction of the rotational engine axis, which is distinctly lower than the heat expansion coefficient of the material of the compressor rotor. The heat expansion coefficient of the material of the inner housing shell is lower in the circumferential direction and approximately equal in the axial direction relative to the heat expansion coefficient of the rotor. The fixed bearing of the compressor rotor ...

A turbine ring assembly with cold setting

A double-casing turbine

... 913,375. Turbines. LICENTIA PATENTVERWALTUNGS-G.m.b.H. May 6, 1959 [May 7, 1958], No. 15535/59. Class 110 (3). A double-casing turbine comprises a sheetmetal outer casing 21 and an inner easing 11 supported by horizontal faces formed on the outer casing. The outer casing 21 is supported by the turbine foundation 13, in a horizontal plane near to its axis, by faces arranged vertically below those faces of the outer casing which support the inner casing and are separated from them solely by the wall thickness of the outer casing. The inner casing rests on the supporting faces of the outer casing by means of supporting arms 14 enclosed in pockets 16 formed in the outer casing.

Improvements in or relating to steam or gas turbines

... 315,351. Akt.-Ges. der Maschinenfabriken Escher, Wyss, et Cie. July 12, 1928, [Convention date]. Casings. - The casing 4 of a high-pressure steam turbine is formed with its outer perimeter prismatic as shown in Fig. 2. The casing is made of forged material and is divided on an axial plane. The ends are closed by plugs 8 which are also divided on an axial plane. The plugs have locking grooves on the periphery, and labyrinth bushes on their inner circumferences.

POWER TURBINE NOZZLE SUPPORT STRUCTURE

FLUID FLOW MACHINE

... 1335939 Turbines KRAFTWERK UNION AG 6 March 1972 10419/72 Heading F1T An arrangement for supporting and centering an internal housing within a surrounding external housing comprises, when applied to a seal housing 6 contained within the high pressure end of a steam turbine housing 4, four equally spaced projections k extending radially in a common transverse plane from seal housing 6 to engage axial grooves n in housing 4, means being provided to retain the projections k in position. Housing 6 is formed in two halves 6a, 6b secured together by screws 6d and is inserted into turbine housing 4, together with rotor 1, from left to right of Fig. 1 until projections k enter grooves n and annular faces r 1 , r 2 on the respective housings abut via shim rings r 3 , r 4 to prevent further leftwards movement. Each groove n is formed by a narrower and a wider portion which define shoulders t 1 against which a wedge a abuts to prevent leftwards movement of projection k, the wedge a having been inserted ...

Improvements in or relating to steam turbines

... 768,069. Turbines, elastic-fluid. WESTINGHOUSE ELECTRIC INTERNATIONAL CO. March 17, 1955 [March 24, 1954], No. 7820/55. Class 110 (3). An axial flow steam turbine having an outer casing 10 surrounding an inner casing 14 has formed in the inner casing 14 an annular chamber 27 which communicates with an intermediate pressure stage 19a of the turbine in order to reduce the pressure and temperature differentials across-the walls of the turbine. The chamber 27 communicates through restricted passages 32, 32a with conduits 33 to lead the steam back to a lower pressure stage 19b, or the steam may be used for any other purpose. Steam is discharged from the lowest pressure stage into an annular chamber 29 between the inner and outer casings 14, 10 and is exhausted through a connection 30. Steam inlet connections 20 in the outer casing 10 are slidably mounted in extensions 21 in the inner casing to allow for thermal expansion. An annular groove 34 extends from the junction of the restricted passages ...

Internal insulation for high-temperature steam turbines

INNERE ISOLATION FUER HOCHTEMPERATUR-DAMPFTURBINEN

EXHAUST-GAS TURBINE FOR A TURBOCHARGER

INTERNAL ISOLATION FOR HIGH-TEMPERATURE STEAM TURBINES

STEAM TURBINE

Device at radial steam or gas turbines to reconciliation according to the heating up developing axial expansion of the internal or outside parts connected with the turbine case.

Over pipings and valves fed gas turbine

Low pressure turbine with two independent condensing systems

A low-pressure turbine and a steam power plant with a low-pressure turbine (1) is suggested that is connected to an additional condensing system (25), thus allowing to maintain the electric output at a high level, even if the main condensing system (17) has a reduced capacity due to cooling water restrictions.

MAIN STEAM INLET STRUCTURE

DEVICE FOR FASTENING A BURNER RING IN THE REHEAT COMBUSTION CHAMBER OF A TURBOJET ENGINE

Dispositif de fixation d'un anneau brûleur sur des bras accroche-flammes (14) dans une chambre de postcombustion d'un turboréacteur, l'anneau brûleur étant formé de secteurs d'anneau (12) placés sensiblement bout à bout et dont les extrémités sont reçues et guidées entre deux plaques (34, 36) parallèles à orientation circonférentielle des bras accroche-flammes (14), et sont immobilisées entre ces plaques (34, 36) par des pièces de verrouillage (52) qui sont elles-mêmes retenues entre les plaques (34, 36) par des moyens de blocage (54, 56) engagés dans des orifices (58, 60, 64) alignés des plaques (34, 36) et des pièces de verrouillage (52).

STEAM TURBINES

INSPECTION PORT FOR TURBINES

PROCESS FOR MANUFACTURING A TURBINE STATOR CASING

L invention a pour objet un procédé de fabrication de carter de stator de turbine comprenant les opérations consistant à ménager entre les parois des parties (O1, O2, O3, E1, E2) d'un moule, une cavité de forme correspondant à celle de l'enveloppe dudit carter ; solidariser des noyaux solubles (10), à au moins une desdites parties de moule (E1), ces noyaux étant maintenus à distance de la paroi de cette partie de moule et matérialisant des espaces libres que l'on souhaite ménager à l'intérieur de ladite enveloppe ; mettre en place, entre les noyaux (10), des inserts (20) solubles matérialisant des chemins de circulation entre lesdits espaces libres ; remplir ladite cavité avec une poudre d'un alliage métallique (24) ; fritter cette poudre (24) par compression isostatique à chaud ; éliminer les noyaux (10) et les inserts (20) par dissolution ; et extraire l'enveloppe ainsi moulée. Application à la fabrication d'un carter de stator de turbine de turboréacteur d'avion.

AN AIR-COOLED GAS TURBINE EXHAUST CASING

Cooling air passages are formed in the wall of an exhaust casing connected to a turbine casing of a gas turbine. Low pressure air extracted from the low pressure stage of an air compressor of the gas turbine is supplied to the cooling air passage from the portion near the downstream end of the exhaust casing. Cooling air flows through the cooling air passage toward the upstream end of the exhaust casing and then flows into an annular cavity formed in the turbine casing near the portion corresponding to the last turbine stage. Therefore, the metal temperature of the exhaust casing near the upstream end (near the joint between the exhaust casing and the turbine casing) is lowered by the cooling air and, as cooling air of a relatively high temperature is supplied to the cavity in the turbine casing, the metal temperature of the turbine casing near the downstream end becomes higher than that provided by a conventional cooling system. Therefore, the difference between the metal temperatures ...

AXIAL FLOW ELASTIC FLUID TURBINE WITH INLET SLEEVE VIBRATION INHIBITOR

... -10- W.E. 53,718 An axial flow elastic fluid turbine has a vibration inhibitor for the inlet sleeves which extend through a motive fluid flow area between the inner and outer cylindrical casings of the turbine. The vibration inhibitor comprises a flexible support, preferably in the form of a metal plate, that is secured to, and extends between, adjacent inlet sleeves in the motive fluid flow area between the inner and outer cylindrical casings, and the plates have at least one bend therein in the direction of the radius of the casings to permit flexibility thereof.

HOUSING STRUCTURE FOR AN ELASTIC FLUID UTILIZING MACHINE

STEAM TURBINES

HEAT SHIELD WITH STRESS RELIEVING FEATURE

A heat shield for a fuel member of a gas turbine engine having at least one heat shield segment having a connection edge with at least one joint receiving portion defined therealong for receiving a welded joint attaching the heat shield segment to a fuel member, each joint receiving portion including a stress relieving feature defined along at least one end thereof.

GAS TURBINE AND OPERATION METHOD OF GAS TURBINE COMBINED ELECTRIC GENERATING PLANT, GAS TURBINE COMBINED ELECTRIC GENERATING PLANT, AND COMPUTER PRODUCT

A casing air temperature Ta and a steam temperature Ts are measured, and if an absolute value .DELTA.T of a difference between these two temperatures is within a predetermined temperature, the gas turbine is connected to the generator. After the connection is done, the load is gradually increased, and the coolant changeover signal is sent from a processor to a controller. The coolant is then changed to the steam, thereby completing the connection of the gas turbine with the generator and the changeover of the coolant.

TURBOCHARGER THERMAL ISOLATION CONNECTION

An engine turbocharger includes a thermal isolation connection between a rotor and compressor section support and an exhaust section including an exhaust duct attached to the rotor support. The connection includes spring biased wear pads allowing sliding motion at one or more interfaces between the exhaust duct and the rotor support to accommodate relative radial thermal growth. Radial key and slot guides between the exhaust duct and rotor support maintain axial alignment of the connected components during relative radial motion at the connecting interfaces.

TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH NOZZLE INJECTION FOR A GAS TURBINE ENGINE

A turbine engine shutdown temperature control system (10) configured to limit thermal gradients from being created within an outer casing (12) surrounding a turbine blade assembly (14) during shutdown of a gas turbine engine (16) is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities (18) in the outer casing (12), arched and sway-back bending of the outer casing (12) is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine (16). The turbine engine shutdown temperature control system (10) may operate during the shutdown process where the rotor (26) is still powered by combustion gases or during turning gear system operation after shutdown of the gas turbine engine, or both, to allow the outer casing (12) to uniformly, from top to bottom, cool down.

LINER ASSEMBLY, ENGINE HOUSING, AND METHODS OF ASSEMBLING THE SAME

A liner assembly includes a core and a septum coupled to the core. The liner assembly also includes a facesheet coupled to the septum. The facesheet includes a plurality of slots defined therethrough. Each slot of the plurality of slots includes a major axis oriented perpendicular to a centerline of the liner assembly.

RADIAL FIXING AND POSITIONING FLANGES FOR SHELLS OF AXIAL TURBINE COMPRESSOR HOUSINGS

An axial turbomachine housing is designed to channel a primary annular flow in the low-pressure compressor of the turbomachine. The housing has a first shell and a second shell designed to be contiguous and coaxial. The first shell has a flange and a centring surface substantially cylindrical. The second shell has a flange and radial centring means designed to mate with the centring surface. The flange of the first shell includes cut-outs distributed along its circumference, and the centring means extend axially from the flange of the second shell through the cut-outs to the centring surface where the two flanges are in contact.

COOLING AND SEALING SYSTEM FOR TURBOMACHINERY

Mehrstufige Dampf- oder Gasturbine.

Hochdruck-Dampf- oder Gasturbine.

Dampf- oder Gasturbine, insbesondere für hohe Drücke.

Befestigung von Leitvorrichtungen in Dampf- und Gasturbinen, insbesondere solchen mit achsial ungeteiltem Gehäuse.

Mit elastischem Fluidum arbeitende Turbine.

Turbine, insbesondere für Arbeitsmittel hoher Temperatur.

Turbomaschine, insbesondere für Arbeitsmittel hoher Temperatur.

Dampf- oder Gasturbine.

Beschaufelte Rotationsmaschine.

Kupplung für Rohrleitungen.

Dampfturbine

Kupplungsteil für Schläuche.

Dampf- oder Gasturbine für hohe Drücke und Temperaturen

Dampfturbine mit wenigstens einem in ein ungeteiltes Gehäuse eingesetzten, in einer Axialebene unterteilten Leitschaufelträger

Turbine

Turbine für Dampf oder gasförmige Treibmittel.

Turbine à combustion interne.

Dampfturbine für hohe Drücke und Temperaturen mit in ein Aussengehäuse eingesetztem Leitschaufelträger

Axialdurchströmte Turbine für heisse Treibmittel, insbesondere Gasturbine

Gussgehäuse von Radialströmungsmaschinen

Gehäuse für Gas- oder Dampfturbinen.

Thermische Turbine mit innerem und äusserem Gehäuse.

Turbo-machine

Einrichtung zur Abstützung der beiden Gehäuse von Doppelmantelturbinen

Axialströmungsmaschine für hohen Druck

Wärmeturbine mit Aussen- und Innengehäuse

Mehrstufige, axial beaufschlagte Gleichdruckturbine

In Doppelmantel-Bauweise ausgeführter Niederdruckteil einer Dampfturbine

Turbine

Doppelmantelturbine

Turbine für hocherhitztes gasförmiges Treibmittel

Dampfturbine mit gesteuerter Dampfentnahme

Gasturbinenanlage

Frischdampfzuführung bei mehrflutiger hochbeanspruchter Doppelgehäuse-Turbine

Höchstdruck-Heissdampfturbine

Модуль для паровой турбины

1. Модуль (1) для паровой турбины, содержащий внутренний кожух (5) турбины с, по меньшей мере, одним комплектом неподвижных лопаток, ротор (6), оснащенный, по меньшей мере, одним комплектом лопаток, и плиту (16), при этом внутренний кожух (5) турбины опирается на плиту (16) посредством, по меньшей мере, двух поперечин (20), закрепленных на упомянутом внутреннем кожухе (5) турбины, а соединение между упомянутыми поперечинами (20) и плитой (16) выполнено в виде нескольких механических средств соединения (23), каждое из которых обеспечивает предотвращение подъема внутреннего кожуха (5) турбины относительно плиты (16), а также обеспечивает скольжение упомянутого внутреннего кожуха (5) турбины по подобной плите (16). ! 2. Модуль по п.1, отличающийся тем, что место (22) сопряжения между поперечиной (20) и плитой (16) является, по существу, горизонтальным, при этом каждое средство (23) соединения содержит вертикальную штангу (24), неподвижно закрепленную в плите (16), и оснащено шайбой (30), каждая поперечина (20) опирается на плиту (16) посредством упомянутых штанг (24), проходящих через нее с зазором вдоль места (22) сопряжения, а шайбы (30) расположены над каждой поперечиной (20). ! 3. Модуль по п.2, отличающийся тем, что каждое средство (23) соединения содержит управляющие устройства (27), закрепленные на плите (16) и обеспечивающие локальное регулирование по высоте внутреннего кожуха (5) турбины, при этом каждая поперечина (20) опирается на управляющее устройство (27). ! 4. Модуль по п.3, отличающийся тем, что управляющее устройство является вращательным приводом (27), приводимым в действие в месте (22) сопряжения, после того как поперечина (20) установлена на упомянутое управляющее ус� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 110 410 (13) U1 (51) МПК F01D 25/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ТИТУЛЬНЫЙ ЛИСТ ОПИСАНИЯ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (21)(22) Заявка: 2011114266/28, 12.04.2011 (24) Дата начала отсчета ...

Turbine casing

A casing includes an inner shell and an outer shell that surrounds the inner shell and comprises a plurality of inflection points. An annular flange is between the inner shell and the outer shell, and a plurality of joints attach the inner shell to the annular flange. A connector is between the annular flange and the outer shell at each of the plurality of inflection points. A method for assembling a casing includes joining a plurality of curved sections to one another to generally define an arcuate inner shell and surrounding the arcuate inner shell with an outer shell. The method further includes attaching the arcuate inner shell to an annular flange at first attachment points and connecting the annular flange to the outer shell at second attachment points spaced approximately equidistantly from the first attachment points.

Temperature reducing flange for steam turbine inlets

An intermediate, temperature reducing flange is inserted between an external steam (process) connection flange and first pressure vessel, or outer shell of a turbine or a second pressure vessel, or inner shell of the turbine. The temperature reducing flange has an integral portion that is exposed to an internal turbine area that is at a lower temperature than the steam in the steam inlet port of the turbine. This portion provides for a cooling effect, thus isolating the outer shell of the turbine from the high temperature of the steam pipe. Isolating the highest temperature connections from the remainder of the outer shell allows use of lower cost alloys for the outer shell.

Turbine shell with pin support

A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.

System and method for removing heat from a turbomachine

The present invention provides systems and methods of removing heat from internal areas of a turbomachine. Embodiments of the present invention may incorporate a suction device and a control system. Operatively, these elements may collectively discharge remnants of a heated fluid and/or gas from those internal areas.

Turbine inlet casing with integral bearing housing

The present application provides a compressor inlet casing. The compressor inlet casing may include an inner bellmouth and a bearing housing. The bearing housing may include an integrally cast first half connected to the inner bellmouth and a cavity positioned between the inner bellmouth and the integrally cast first half of the bearing housing.

Flowpath insert and assembly

A flowpath assembly for a gas turbine engine includes a plurality of flowpath insert ducts arranged in a cascade configuration. Each flowpath duct includes a radially inward wall, a radially outward wall, a first side wall, and a second side wall. A flowpath volume is defined between the inward, outward, first side and second side walls. The first side wall of a given one of the plurality of flowpath insert ducts is positioned adjacent to the second sidewall of an adjacent one of the plurality of flowpath insert ducts in the cascade configuration.

Turbomachine including an inner-to-outer turbine casing seal assembly and method

A turbomachine includes an inner casing component having a first end that extends to a second end and a seal member. An outer casing component is coupled to the inner casing component. The annular outer casing component includes a first end portion that extends to a second end portion and a seal element that aligns with the seal member of the annular inner casing component to form a seal passage. A seal is arranged in the seal passage. The seal includes a first end section that extends to a second end section through an intermediate zone. The first end section includes a recessed portion and the second end section includes a connecting portion. The connecting portion is configured and disposed to nest within the recessed portion to form a substantially continuous seal.

Internal Combustion Engine Cylinder Head With Integral Exhaust Runners And Turbocharger Housing

An internal combustion engine cylinder head is based upon a one-piece structure including a number of exhaust runners, an exhaust collector, and a turbocharger exhaust turbine housing, all formed as one-piece.

Method of measuring steam turbine, measuring device, and method of manufacturing steam turbine

A method of measuring a steam turbine according to an embodiment has: installing a measuring device into the inside of the steam turbine through an inspection hole or a manhole of the steam turbine or an inspection hole or a manhole of a condenser connected to the steam turbine, when the steam turbine is halted; and measuring a position and a dimension of an axial key or a center key of the steam turbine by using the measuring device, without opening a turbine casing of the steam turbine.

DOUBLE-WALLED TURBOCHARGER HOUSING, FLANGE AND CONNECTION THEREOF

A double-walled turbocharger housing made of sheet metal includes an inner sheet metal shell which conducts hot exhaust gases and a relatively cold outer sheet metal shell which is spaced apart from the inner sheet metal shell via an air gap. The double-walled turbocharger housing is connected to a bearing flange with a circumferential collar via a common welding seam. The bearing flange is provided with a collar on an outside which faces away from the hot exhaust gas. An outer end of the inner sheet metal shell is provided with a collar with which it embraces the outer sheet metal shell. Both sheet metal shells are connected with the collar of the bearing flange via a common welding seam, wherein an air gap is present between the inner sheet metal shell and the outer sheet metal shell up to the outer end of the inner sheet metal shell. 1. In combination:a double walled turbocharger housing, comprising an inner sheet metal shell, and an outer sheet metal shell spaced apart from the inner sheet metal shell via an air gap, said inner sheet metal shell having a collar on an outer end and embracing the outer sheet metal shell with the collar, said air gap extending up to an outer end of the inner sheet metal shell;a bearing flange having a collar on an outside facing away from hot exhaust gas; anda welding seam, joining the inner sheet metal shell and the outer sheet metal shell to the collar of the bearing flange.2. The combination of claim 1 , wherein the turbocharger housing is constructed for connection to a rotor group with adjustable turbine geometry via the bearing flange.3. The combination of claim 1 , wherein the air gap on the outer end of the inner sheet metal shell has a width of at least 1 mm.4. The combination of claim 1 , wherein the collar of the inner sheet metal shell is clamped between the outer sheet metal shell and the collar of the bearing flange.5. The combination of claim 4 , wherein the collar of the inner sheet metal shell is clamped between ...

EXPANSION JOINT AND STEAM TURBINE SYSTEM INCLUDING THE SAME

An expansion joint that is provided between a steam turbine outlet and a condenser inlet, including: an upstream baffle tube that has one end secured to an upstream fixing end and the other end as a free end, and forms a steam channel; a downstream baffle tube that has one end secured to a downstream fixed end and the other end as a free end, the free end being relatively movable outside the free end of the upstream baffle tube; and a flexible cylinder that is formed of a non-metal material using a resin sheet, and deformable while airtightly surrounding the baffle tubes. 1. An expansion joint provided between a steam turbine outlet and a condenser inlet , comprising:an inner metal cylinder that has one end secured to an upstream fixing end and the other end as a free end, and that forms a steam channel;an outer metal cylinder that has one end secured to a downstream fixed end and the other end as a free end, the free end being movable relative to the inner metal cylinder at a radial outside of the free end of the inner metal cylinder; anda flexible cylinder that is formed of a non-metal material using a resin sheet and that is deformable while airtightly surrounding an outer portions of the inner metal cylinder and an outer portions of the outer metal cylinder.2. The expansion joint according to claim 1 , wherein the flexible cylinder includes a glass cloth stacked on the resin sheet.3. The expansion joint according to claim 1 , wherein the steam turbine and the condenser are components of a steam turbine system for driving machines mounted on a floating body or a ship for treating liquefied gas.4. A steam turbine system comprising:a steam turbine rotationally driven by steam;a condenser that condenses steam discharged from the steam turbine; and{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'an expansion joint which is configured according to and which is provided between the steam turbine and the condenser.'} The present invention relates to an expansion joint ...

HEAT SHIELD FOR A LOW-PRESSURE TURBINE STEAM INLET DUCT

The present invention relates to an assembly comprising a duct, preferably a turbine duct, and at least one segment formed of at least two rigid shells, each shell comprising at least one fixing orifice for fixing to the duct and at least one fixing element at least one boss per shell which boss is fixed to the duct and against which boss the shell rests, such that at least one orifice and one boss face one another, and that the fixing element passes through the orifice facing the boss and is fixed to the boss. 1. An assembly comprising:a duct,and at least one segment formed of at least two rigid shells, each shell comprising at least one fixing orifice for fixing to the duct and at least one fixing element, wherein:the duct comprises at least one boss per shell, which boss is fixed to the duct and against which boss the shell rests,at least one orifice and one boss face one another, andthe fixing element passes through the orifice facing the boss andthe fixing element is fixed to the boss.2. The assembly according to claim 1 , wherein a first of the shells has a rim on one lateral edge to overlap a lateral edge of another of the shells.3. The assembly according to claim 1 , wherein each boss is surmounted by a cap.4. The assembly according to further comprising at least one partition between a first and a second boss claim 1 , the partition being welded to at least the first boss and having a height smaller than that of the first boss.5. The assembly according to further comprising an overlapping element joined to at least one shell of a first segment of the assembly and overlapping one end of a shell of a second segment.6. The assembly according to wherein each segment and the duct between them define a space of constant height.7. The assembly according to wherein each segment and the duct between them define a space filled with air.8. The assembly according to wherein the overlapping element is T-shaped.9. A turbine comprising an outer casing claim 5 , an inner ...

COMBUSTOR TRANSITION DUCT ASSEMBLY WITH INNER LINER

A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced. 1. A transition duct assembly for a turbine engine comprising:a transition duct having a hollow body with an inner peripheral surface and an outer peripheral surface, the transition duct having an inlet and an outlet, the transition duct having an inlet end and an outlet end, the inner peripheral surface of the transition duct being convergent along a majority of the transition duct when moving from the inlet end to the outlet end thereof; andan inner liner removably received within the transition duct, the inner liner having a generally hollow body with an inner peripheral surface and an outer peripheral surface, the outer peripheral surface of the inner liner being correspondingly convergent to the inner peripheral surface of the transition duct, and the inner peripheral surface defining an internal flow passage through the assembly.2. The transition duct system of wherein the transition duct is made of a different material than the inner liner.3. The transition duct system of wherein the inlet end of the transition duct includes a flange claim 1 , wherein the inlet end of the inner liner includes a ...

Turbine shell with pin support

A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.

STEAM TURBINE SHELL DEFLECTION FAULT-TOLERANT CONTROL SYSTEM, COMPUTER PROGRAM PRODUCT AND RELATED METHODS

Various approaches include: obtaining temperature data indicating temperatures of distinct zones in an upper half of a steam turbine shell and a lower half of a steam turbine shell; determining whether a difference between a temperature of a zone in the upper half of the steam turbine shell and a temperature of a neighboring zone in the lower half of the steam turbine shell exceeds a threshold; and initiating a change in a state of a thermal element in at least one of an adjacent zone to at least one of the zone in the upper half of the steam turbine shell or the neighboring zone in the lower half of the steam turbine shell in response to determining the difference exceeds the threshold. 1. A system comprising: obtaining temperature data indicating temperatures of distinct zones in the upper half of the steam turbine shell and the lower half of the steam turbine shell, the thermal element having corresponding distinct zones as the upper half of the steam turbine shell and the lower half of the steam turbine shell;', 'determining whether a difference between a temperature of a zone in the upper half of the steam turbine shell and a temperature of a neighboring zone in the lower half of the steam turbine shell exceeds a threshold; and', 'initiating a change in the state of the thermal element in at least one of an adjacent zone to at least one of the zone in the upper half of the steam turbine shell or the neighboring zone in the lower half of the steam turbine shell in response to determining the difference exceeds the threshold., 'at least one computing device configured to control a state of a thermal element in contact with a steam turbine shell having an upper half and a lower half, by performing actions including2. The system of claim 1 , wherein the distinct zones includes approximately ten zones in the upper half of the steam turbine shell and approximately ten zones in the lower half of the steam turbine shell.3. The system of claim 1 , wherein the at least ...

Nacelle compression rods

A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine. The compression rod may transmit loads between halves of the core cowl. The spring may cause the plunger to extend and contract in response to vibrations or other relative movement between halves of the core cowl.

Unducted propeller turboshaft engine provided with a reinforcing shell integrating pipe segments

An airplane unducted propeller turboshaft engine having a gas generator and a receiver including a propulsion assembly carrying least one propeller, the engine including a first casing, a second casing, and a third casing, the third casing being provided between the first and second casings and surrounding at least a portion of the gas generator, a reinforcing shell presenting a first attachment zone mounted on the first casing second attachment zone mounted on the second casing, and a wall provided between the first and second attachment zones and surrounding the third casing, wherein the reinforcing shell further includes at least one pipe segment integrated in the wall.

Gas turbine engine attachment structure and method therefor

An attachment structure for a gas turbine engine includes a frame that has a first annular case. A second annular case extends around the frame. The first annular case and the second annular case include a plurality of interlocks. Each of the interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second case. The first member is received in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.

Exhaust system having a flow path liner supported by structural duct segments

The exhaust system ( 60 ) includes an exhaust flow path liner ( 62 ) surrounded and supported by a plurality of structural duct segments ( 64, 70 ). Pluralities of links ( 84 ) are secured to and extend between the duct segments ( 64, 70 ) and the liner ( 62 ). A duct end ( 88 ) of the link includes a lock member ( 96 ) having a diameter greater than a width of the stem ( 86 ). The lock member ( 96 ) is configured to be secured within a capture nest ( 98 ) defined between and within adjacent junction flanges ( 76, 80 } of the structural duct segments { 64, 70 ) when the segments ( 64, 70 ) are secured to each other to secure the segments ( 64, 70 ) together. A catch member ( 100 ) at an opposed end of the link ( 84 ) is secured to a capture node ( 102 ) at the exhaust liner ( 62 ).

Method of disassembling and assembling gas turbine and gas turbine assembled thereby

A method of assembling and disassembling a gas turbine, and a gas turbine assembled thereby, improves work efficiency and reduces time and cost by carrying out various disassembly and reassembly processes depending on circumstances. In one process, a turbine section is disassembled from a gas turbine by sequential steps of disassembling an upper turbine case; disassembling a rear diffuser assembly and a rear bearing assembly; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly. In another process, first-stage to fourth-stage blade assemblies and first-stage to fourth-stage vane assemblies in a turbine section are disassembled from the gas turbine by sequential steps of disassembling an upper turbine case; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly. The gas turbine includes a compressor section, a combustor section, and the turbine section assembled in a reverse order with respect to the disassembly method.

Pressure casing of a turbomachine

The invention relates to a pressure casing, which includes a plurality of casing shells which are connected in a pressure-tight manner in a parting plane by means of a flange. The casing shells are pressed together with sealing effect in the parting plane in the region of the flange by means of at least one threaded bolt which extends in a through hole through the flange perpendicularly to the parting plane. Reduced temperature differences between the flange and the connecting bolts of the flanged joint are achieved by the at least one threaded bolt being charged with a heat transfer medium over a part of its length. The heat transfer medium is supplied via holes extending through the flange.

TURBOFAN ENGINE COMPRISING AN OUTLET CONE COOLED BY ITS SECONDARY FLOW

A turbofan engine including an exhaust casing traversed by a primary flow and surrounded by a secondary flow and an outlet cone carried by this exhaust casing, the exhaust casing and the outlet cone together defining an internal space. The exhaust casing includes a hollow radial arm traversing the primary flow in order to convey part of the secondary flow so as to form a cooling flow for supplying the internal space, and the outlet cone is terminated by an opening for discharging the cooling flow. 17-. (canceled)82123252123213823. A turbofan engine including an exhaust casing () through which passes a primary flow (FP) and surrounded by a secondary flow (FS) both circulating from upstream (AM) to downstream (AV) of the turbofan engine during operation , and an outlet cone () having an upstream end () carried by this exhaust casing () , the outlet cone () delimiting an inner space (E) , wherein the exhaust casing () includes a hollow radial arm () crossing the primary flow (FP) which conveys part of the secondary flow (FS) in order to form a cooling flow (Fr) to cool down one or several component(s) located in the inner space (E) , and in that the outlet cone () terminates in an opening (S) for discharging the cooling flow (Fr).92341424141. The turbofan engine according to claim 8 , wherein the outlet cone () includes a main wall () and an inner lining wall () which runs along the main wall () while being spaced therefrom so as to delimit claim 8 , together with this main wall () claim 8 , an inter-wall space (Ei) claim 8 , and wherein a portion of the cooling flow (Fr) passes through the inter-wall space (Ei) before being discharged by the outlet opening (S).1038. The turbofan engine according to claim 8 , wherein the radial arm () terminates in a scoop soaking in the secondary flow (FS) to promote sampling of the cooling flow (Fr).1123. The turbofan engine according to claim 8 , wherein the outlet (S) is formed by a cylindrical extension of the cone (). ...

NACELLE COMPRESSION RODS

A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine. The compression rod may transmit loads between halves of the core cowl. The spring may cause the plunger to extend and contract in response to vibrations or other relative movement between halves of the core cowl. 1. An aircraft nacelle comprising:a first half comprising a first engagement feature, and a second half comprising a second engagement feature, wherein the first half and the second half are rotatable about a hinge between a closed position in which the first half and the second half enclose a portion of an aircraft engine, and an open position in which the first half and the second half are separated and allow access to the portion of the aircraft engine; and a proximal end and a distal end, wherein in response to the aircraft nacelle being in the closed position, the proximal end is in contact with the first engagement feature and the distal end is in contact with the second engagement feature; and', 'a spring configured to bias the proximal end apart from the distal end, wherein, in response to the aircraft nacelle being in the closed position, the spring is in a compressed position., 'a compression rod comprising2. The aircraft nacelle of claim 1 , wherein the compression rod comprises a plunger.3. The aircraft nacelle of claim 1 , wherein the compression rod comprises a compression tube.4. The aircraft nacelle of claim 3 , wherein the compression tube comprises a plunger bore.5. The aircraft nacelle of claim 4 , wherein the spring is located within the plunger bore.6. The aircraft nacelle of claim 3 , wherein the compression tube comprises a threaded bore.7. The aircraft nacelle of claim 6 , wherein the proximal end comprises a threaded shaft located within the threaded bore.8. The aircraft nacelle of claim further comprising a pylon bracket claim 6 , wherein the ...

CASE COUPLING AND ASSEMBLY

A system and method for coupling cases associated with an engine of an aircraft. A first case includes a first plurality of threads. A second case includes a second plurality of threads. A coupler includes a third plurality of threads and a fourth plurality of threads. An interface is configured to align the first case and the second case before the first plurality of threads engage the third plurality of threads or the second plurality of threads engage the fourth plurality of threads. 1. A method for coupling cases associated with an engine of an aircraft , comprising:joining a first bracket with a first case and a second bracket with a second case;threading an alignment pin into the second bracket;bringing the first case and the second case together until contact is made with threads of a coupler, wherein the contact occurs subsequent to an engagement of the alignment pin with the first bracket; andapplying torque to the coupler to cause the first case to couple to the second case.2. The method of claim 1 , further comprising:unthreading and removing the alignment pin from the first bracket and the second bracket subsequent to applying the torque; andremoving the first bracket from the first case and the second bracket from the second case subsequent to the removal of the alignment pin.3. The method of claim 1 , wherein the joining of the first bracket with the first case includes bolting the first bracket to the first case.4. The method of claim 1 , further comprising:joining a third bracket with the first case and a fourth bracket with the second case; andthreading a depth pin into the fourth bracket.5. The method of claim 4 , further comprising:threading a gauge into the third bracket.6. The method of claim 5 , further comprising:adjusting the gauge to contact the depth pin; andrecording a reading associated with a depth based on the adjustment of the gauge.7. The method of claim 6 , further comprising:pulling apart the first case and the second case; ...

EXPANSION JOINT AND METHODS OF ASSEMBLING THE SAME

An expansion joint for use between a turbine duct and a diffuser duct includes a first flange coupled to the turbine duct, a second flange coupled to the diffuser duct, and a flexible element positioned between and coupled to the first flange of the turbine duct and the second flange of the diffuser duct. The flexible element defines a trough for receiving a liquid therein. The trough includes a drain pipe configured to channel the liquid away from the trough. 1. An expansion joint for use between a turbine duct and a diffuser duct , said expansion joint comprising:a first flange coupled to the turbine duct;a second flange coupled to the diffuser duct; anda flexible element positioned between and coupled to said first flange of the turbine duct and said second flange of the diffuser duct, said flexible element defining a trough for receiving a liquid therein, said trough comprising a drain pipe configured to channel the liquid away from said trough.2. The expansion joint in accordance with claim 1 , wherein said flexible element comprises a plurality of flexible seals coupled to said first flange and said second flange.3. The expansion joint in accordance with claim 2 , wherein each flexible seal of said plurality of flexible seals is formed from a single sheet component and comprises a curved profile shape comprising at least one bend radius having a radius selected to reduce a stress and strain of said each flexible seal.4. The expansion joint in accordance with claim 3 , wherein said each flexible seal comprises a plurality of apertures therein.5. The expansion joint in accordance with claim 2 , wherein said plurality of flexible seals comprises a first layer of flexible seals forming a first complete circumferential array claim 2 , and a second layer of flexible seals forming a second complete circumferential array claim 2 , wherein each flexible seal of said second layer of flexible seals overlaps a radial seam defined between adjacent flexible seals of said ...

OVERLOAD INTRODUCTION INTO A STEAM TURBINE

An assembly with a steam turbine and an overload valve, wherein the overload valve is arranged opposite the fresh steam valve and a fresh steam flows partially through the flow channel and partially into an overload inflow region via the overload valve. 1. An assembly comprising:a steam turbine with a two-shell casing which comprises an outer casing and an inner casing arranged therein, and a connection guided through the outer casing,wherein the connection is designed with a pair of connection openings formed by a first connection opening and a second connection opening which are formed on the inner casing, further comprising a first valve for feeding steam into the inner casing, wherein the first valve is fluidically connected to the first connection opening, further comprising a second valve for discharging steam, wherein the second valve is fluidically connected to the second connection opening,wherein the steam turbine further has an overload inflow region which is fluidically connected to the second valve,wherein the steam turbine has a blading region which is configured for a flow direction, and the overload inflow region opens into the blading region after a blade stage situated downstream in the flow direction,wherein the connection openings are formed oppositely on the inner casing.2. The assembly as claimed in claim 1 ,wherein the steam turbine is of two-flow configuration, formed by a first flow channel and a second flow channel.3. The assembly as claimed in claim 2 ,wherein the first and second valve are arranged on the first flow channel.4. A method for operating a steam turbine in overload operation claim 2 , comprising:operating the steam turbine such that steam flows into the inflow region of the steam turbine via a first valve and flows partially into a blading region and partially out of the steam turbine via a second valve in an overload line and from there flows into the steam turbine into an overload inflow region situated downstream,wherein ...

ELECTRIC MOTOR HAVING AN INTEGRATED COOLING SYSTEM AND METHODS OF COOLING AN ELECTRIC MOTOR

The present disclosure pertains to electric machines such as electric propulsion systems for aircraft that integrated cooling systems, and methods of cooling such an electric machine. Exemplary electric machines include an electric motor that has a stator, a rotor, and a drive shaft operably coupled to the rotor. Exemplary electric machines further include a motor cooling conduit that defines a pathway for conveying a cooling fluid through or around at least a portion of the electric motor, a casing assembly that circumferentially surrounds at least a portion of the electric motor, a casing assembly conduit integrally formed within at least a portion of the casing assembly which defines a pathway for conveying the cooling fluid through the at least a portion of the casing assembly, and a pump or compressor operably coupled to the drive shaft and configured to circulate the cooling fluid through the motor cooling conduit and the casing assembly conduit. 1. An electric machine having an integrated cooling system , the electric machine comprising:an electric motor comprising a stator, a rotor, and a drive shaft operably coupled to the rotor;a motor cooling conduit that defines a pathway for conveying a cooling fluid through or around at least a portion of the electric motor, the motor cooling conduit having a thermally conductive relationship with the at least a portion of the electric motor; an annular casing;', 'a plurality of support members extending radially from the annular casing and circumferentially spaced relative to the annular casing; and', 'a casing assembly conduit integrally formed within at least a portion of the casing assembly, the casing assembly conduit defining a pathway for conveying the cooling fluid through the at least a portion of the casing assembly, the casing assembly circumferentially surrounding at least a portion of the electric motor, and the casing assembly conduit having a thermally conductive relationship with an external surface of ...

AUGMENTED COOLING SYSTEM

An apparatus and method for cooling a dual, walled component is disclosed herein. An augmented cooling system according to the present disclosure includes transporting a cooling fluid through one wall of a cooling pathway formed between two opposing spaced apart walls of the dual walled component. The cooling fluid can be deflected away from one wall of the cooling pathway with a first trip strip as the cooling fluid traverses along the cooling pathway. The cooling fluid can be deflected away from the opposing wall of the cooling pathway with a second trip strip as the cooling fluid continues traversing along the cooling pathway. The cooling fluid can then be discharged from the cooling pathway through the opposing wall of the dual walled component. 1. A cooling system comprising:a component having an inner wall and an outer wall spaced apart from one another;a plurality of pedestals extending between the inner and outer walls;a plurality of inner trip strips projecting from the inner wall towards the outer wall at a predetermined height;a plurality of outer trip strips projecting from the outer wall towards the inner wall at a predetermined height,wherein one of either an inner trip strip or an outer trip strip extends between adjacent pedestals;at least one inlet through aperture formed in the inner wall of the component operable for transporting a cooling fluid into a space between the inner and outer walls of the component; anda plurality of outlet through apertures formed in the outer wall of the component operable for transporting the cooling fluid out of the space between the inner and the outer walls of the component;wherein at least one of the inlet through apertures and outlet through apertures is located in one of an inner well and an outer well, respectively, wherein the inner well is bounded on all sides by a plurality of inner trip strips, and wherein the outer well is bounded on all sides by a plurality of outer trip strips.2. The cooling system of ...

COMPLIANT INTERMEDIATE COMPONENT OF A GAS TURBINE ENGINE

One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component. The first component may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure. 1. An apparatus comprising:a first gas turbine engine component structured for use in a gas turbine engine and having a first mating portion;a second gas turbine engine component having a second mating portion formed to receive within it the first mating portion of the first component to interlockingly secure the first component for use during operation of the gas turbine engine; anda load bearing intermediate component positioned between the first mating portion of the first component and the second mating portion of the second component, the load bearing intermediate component including:a main body having a portion configured to bear a loading imparted by contact between the first mating portion and the second mating portion, the main body captured on one of the first mating portion and the second mating portion through a plurality of finger portions extending from the main body.2. The apparatus of claim 1 , wherein the first gas turbine engine component has a different coefficient of thermal expansion than a coefficient of thermal expansion of the second gas turbine engine component.3. The apparatus of claim 2 , wherein the first gas turbine engine component is a ceramic matrix composite claim 2 , wherein the portion of the main body is curved claim 2 , and wherein the curved portion of the main body bears a loading imparted by contact between an arcuate portion of the first mating portion and an arcuate portion of the second mating portion.4. The apparatus of claim 3 , wherein a first finger portion of the plurality of finger portions is disposed opposite a second finger portion of the ...

TURBINE HOUSING AND TURBOCHARGER

A turbine housing has: a first inner member; a second inner member contacting with the first inner member; a turbine scroll flow path enclosed and defined by the first inner member and the second inner member; a first casting housing covering the first inner member at a side opposite to the second inner member; a second casting housing covering the second inner member at a side opposite to the first inner member; an aperture formed in one or both of the first casting housing and the second casting housing and including an opening that opens to an outside; a tube member arranged in the aperture and defining an inlet flow path connected to the turbine scroll flow path; and an inner opening defined by the first inner member and the second inner member and overlapping with one end of the tube member. 1. A turbine housing comprising:a first inner member;a second inner member contacting with the first inner member;a turbine scroll flow path enclosed and defined by the first inner member and the second inner member;a first casting housing covering the first inner member at a side opposite to the second inner member;a second casting housing covering the second inner member at a side opposite to the first inner member;an aperture formed in one or both of the first casting housing and the second casting housing and including an opening that opens to an outside;a tube member arranged in the aperture and defining an inlet flow path connected to the turbine scroll flow path; andan inner opening defined by the first inner member and the second inner member and overlapping with one end of the tube member.2. The turbine housing according to claim 1 , comprising:a first cooling flow path formed in the first casting housing, a cooling medium passing through the first cooling flow path; anda second cooling flow path formed in the second casting housing, a cooling medium passing through the second cooling flow path.3. The turbine housing according to claim 2 , wherein the first and ...

ASSEMBLY FOR SEALING A GAP BETWEEN COMPONENTS OF A TURBINE ENGINE

An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface.

TURBOCHARGER

A turbocharger includes: a turbine wheel; a turbine housing; a bearing housing; a shroud having a facing surface which faces a tip of a blade of the turbine wheel and being configured to surround the turbine wheel, the shroud comprising a separate member from the turbine housing and being disposed inside the turbine housing via a gap with respect to the turbine housing; a mount supported to at least one of the turbine housing or the bearing housing, at a position closer to the bearing housing than a scroll flow path in an axial direction of the turbine wheel; and at least one connection part connecting the mount and the shroud. 114-. (canceled)15. A turbocharger , comprising:a turbine wheel configured to be rotated by exhaust gas of an engine;a turbine housing which accommodates the turbine housing and forms at least a part of a scroll flow path through which exhaust gas to be supplied to the turbine wheel flows;a bearing housing which accommodates a bearing supporting a shaft of the turbine wheel rotatably, the bearing housing being coupled to the turbine housing;a shroud having a facing surface which faces a tip of a blade of the turbine wheel and being configured to surround the turbine wheel, the shroud comprising a separate member from the turbine housing and being disposed inside the turbine housing via a gap with respect to the turbine housing;a mount supported to at least one of the turbine housing or the bearing housing, at a position closer to the bearing housing than the scroll flow path in an axial direction of the turbine wheel; andat least one connection part connecting the mount and the shroud,wherein the turbine housing includes a first housing formed of sheet metal, the first housing accommodating the turbine wheel and forming at least a part of the scroll flow path, andwherein the shroud is disposed inside the first housing via the gap with respect to the first housing.16. The turbocharger according to claim 15 , wherein each of the connection part ...

CONTAINMENT CASING AND GAS TURBINE ENGINE

It is described a containment casing, in particular a containment casing of a gas turbine engine of an aircraft engine, which at least regionally has a structure selected from at least one of the structure types beam structure, cylinder structure, strips cage structure, foam structure, honeycomb structure, corrugated structure or net structure, each of which is formed from SMA. Furthermore, a gas turbine engine including an impactor containment casing is proposed. 1. A containment casing , in particular a containment casing of a gas turbine engine of an aircraft engine , which at least regionally has a structure selected from at least one of the structure types beam structure , cylinder structure , strips cage structure , foam structure , honeycomb structure , corrugated structure or net structure , each of which is formed from SMA.2. The containment casing of claim 1 , wherein said containment casing having at least one layer comprising at least one of said structures.3. The containment casing of claim 2 , wherein the layer comprising a top layer and a bottom layer between which the at least one structure is arranged.4. The containment casing of claim 1 , wherein beams of the beam structure have a conical claim 1 , a cylindrical or an elliptical cross-section.5. The containment casing of claim 1 , wherein the beams consist of solid material and/or are provided with at least one cavity.6. The containment casing of claim 1 , wherein the structure is made by 3D-printing.7. The containment casing of claim 1 , wherein the containment casing is at least approximately hollow cylindrical and the longitudinal axes of the beams are arranged in a radial direction or in an axial direction of the containment casing within the layer.8. The containment casing of claim 1 , wherein the outer sides of the beams are spaced apart to each other or touch each other at least in certain areas.9. The containment casing of claim 1 , wherein the longitudinal axes of the beams are arranged ...

BALANCE BRACKET

A balance bracket for a diffuser case of gas turbine engine is disclosed. In various embodiments, the balance bracket includes a first portion configured for mounting to a first boss on the diffuser case, a second portion configured for mounting to a second boss on the diffuser case, the second portion spaced a distance from the first portion, and a first undulating portion positioned intermediate the first portion and the second portion. 1. A balance bracket for a diffuser case of a gas turbine engine , comprising:a first bracket portion configured for mounting to a first boss on the diffuser case;a second bracket portion configured for mounting to a second boss on the diffuser case, the second bracket portion spaced a distance from the first bracket portion; anda first undulating portion positioned intermediate the first bracket portion and the second bracket portion.2. The balance bracket of claim 1 , wherein the first undulating portion defines a first thickness in a thickness cross section and wherein the first thickness is less than or equal in value to a nominal thickness of the first bracket portion of the balance bracket.3. The balance bracket of claim 2 , wherein the first undulating portion includes a C-shape in the thickness cross section.4. The balance bracket of claim 2 , wherein the first undulating portion includes a S-shape in the thickness cross section.5. The balance bracket of claim 1 , wherein the first undulating portion defines a first width in a width cross section and wherein the first width is less than or equal in value to a nominal width of the first bracket portion of the balance bracket.6. The balance bracket of claim 5 , wherein the first undulating portion includes an hourglass shape in the width cross section.7. The balance bracket of claim 5 , wherein the first undulating portion includes a double hourglass shape in the width cross section.8. The balance bracket of claim 1 , wherein the first undulating portion defines a first ...

COMPRESSOR ASSEMBLY FOR GAS TURBINE

A compressor assembly, and more in general relates to a compressor for a gas turbine providing a solution that teaches to locate within a cavity formed by the outer casing of the compressor and the inner vane carrier a separator element, or membrane, such to divide the cavity into two sub-cavities. This advantageously results in a more flexible design with respect to the positioning of the flange blow-off extractor and to the cavity sizing, as the flange position is not necessarily the boundary for the flow anymore as it would be without the separator element. 1. A compressor assembly for a compressor of a gas turbine , the compressor assembly comprising:a compressor outer casing comprising at least one blow-off opening;a vane carrier defining a bleed duct;wherein the compressor assembly is arranged such that the outer casing and the vane carrier define a cavity for gathering a flow of fluid, said cavity being adapted to receive the fluid through said bleed duct and to feed the fluid externally through said blow-off opening; andwherein the compressor assembly includes a separator element located in said cavity such to divide said cavity in two sub-cavities.2. The compressor assembly according to claim 1 , wherein said separator element extends along a radial direction R of the compressor.3. The compressor assembly according to claim 1 , wherein said separator element is arranged between said outer casing and said vane carrier.4. The compressor assembly according to claim 1 , wherein at least an inner wall of the cavity is covered with a thermally insulating layer.5. The compressor assembly according claim 1 , wherein said thermally insulating layer comprises a coating material.6. The compressor assembly according to claim 1 , wherein said coating material is a ceramic-based coating.7. The compressor assembly according to claim 4 , wherein said thermally insulating layer comprises a metal sheet positioned on said inner wall of the cavity claim 4 , said inner wall ...

SEALING CONFIGURATION TO REDUCE AIR LEAKAGE

A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a boot seal configured to surround a length of the fluid transfer tube, the boot seal having a first end and a second end and a seal ring disposed at the first end, an attachment ring configured to mate with the seal ring and to secure the seal ring against a casing, an annular ring configured to mate with an interior surface of the boot seal at the second end and to surround a portion of the fluid transfer tube, and a clamp ring configured to surround the second end of the boot seal proximate the annular ring. 1. A seal assembly for a fluid transfer tube in a gas turbine engine , comprising:a boot seal configured to surround a length of the fluid transfer tube, the boot seal having a first end and a second end and a seal ring disposed at the first end;an attachment ring configured to mate with the seal ring and to secure the seal ring against a casing;an annular ring configured to mate with an interior surface of the boot seal at the second end and to surround a portion of the fluid transfer tube; anda clamp ring configured to surround the second end of the boot seal proximate the annular ring.2. The seal assembly of claim 1 , wherein the boot seal is constructed of an elastomeric material.3. The seal assembly of claim 2 , wherein the attachment ring is constructed of a metallic material.4. The seal assembly of claim 3 , wherein the annular ring is constructed of one of an aluminum alloy and a titanium alloy.5. The seal assembly of claim 1 , wherein the annular ring comprises a first split ring and a second split ring.6. The seal assembly of claim 5 , further comprising a set screw configured to secure the first split ring to the second split ring.7. The seal assembly of claim 5 , wherein both the seal ring and the attachment ring include a plurality of holes extending there through and configured for attaching the boot seal to the ...

CASTELLATED LATCH MECHANISM FOR A GAS TURBINE ENGINE

A gas turbine engine includes a fan duct including a fan duct inner structure that surrounds a core engine, a fan case that surrounds a fan, a core engine frame, and at least one mechanism configured to secure a portion of the fan duct inner structure to a portion of the core engine frame. The at least one mechanism includes a castellated arcuate portion mounted to one of the fan duct inner structure and the core engine frame and an inwardly projecting retaining feature mounted to the other of the fan duct inner structure and the core engine frame. The castellated arcuate portion is rotatable about an engine central longitudinal axis to position a feature of the castellated arcuate portion proximate to a portion of the inwardly projecting retaining feature to latch the fan duct inner structure. 1. A gas turbine engine comprising:a fan duct including a fan duct inner structure that surrounds a core engine;a fan case that surrounds a fan;a core engine frame; andat least one mechanism configured to secure a portion of the fan duct inner structure to a portion of the core engine frame, wherein the at least one mechanism includes a castellated arcuate portion mounted to one of the fan duct inner structure and the core engine frame and an inwardly projecting retaining feature mounted to the other of the fan duct inner structure and the core engine frame,wherein the castellated arcuate portion is rotatable about an engine central longitudinal axis to position a feature of the castellated arcuate portion proximate to a portion of the inwardly projecting retaining feature to latch the fan duct inner structure.2. The gas turbine engine as recited in wherein the castellated arcuate portion is mounted to the core engine frame and the inwardly projecting retaining feature is mounted to the fan duct inner structure.3. The gas turbine engine as recited in wherein the feature is a tab claim 2 , the inwardly projecting retaining feature includes an inwardly projecting stem and a ...

Mechanism for indicating position of a latch mechanism for an aircraft nacelle

An aircraft nacelle is disclosed and includes a first fan cowl and a second fan cowl. An opening is defined in an exterior surface of the first fan cowl. The aircraft nacelle also includes a blade, a latch mechanism, an arm, and a linkage assembly operably connecting the arm to the blade. The blade is moveable along between a stowed position and a deployed position. The latch mechanism is moveable between a latched position an unlatched position where a portion of the latch mechanism obstructs a path of movement of the blade. The arm is unable to move from an extended position where a portion of the arm extends through the opening in the exterior surface of the aircraft nacelle into a retracted position within an interior volume of the aircraft nacelle when the blade is in the deployed position and the latch mechanism is in the unlatched position.

AIRCRAFT COMPONENT AND GAS TURBINE ENGINE FOR AIRCRAFT

An aircraft component is used in a gas turbine engine for an aircraft. The aircraft component includes an annular part having an outer peripheral surface, and a boss part protruding from the outer peripheral surface of the annular part in a radial direction. In the boss part, at least two through-holes are formed to penetrate the boss part in the radial direction at predetermined intervals. In the boss part around the two through-holes, a cut-out part where a part of the boss part is cut out is formed. 1. An aircraft component used in a gas turbine engine for an aircraft , the aircraft component comprising:an annular part having an outer peripheral surface; anda boss part protruding from the outer peripheral surface of the annular part in a radial direction, whereinin the boss part, at least two through-holes are formed to penetrate the boss part in the radial direction at predetermined intervals,in the boss part around the two through-holes, a cut-out part where a part of the boss part is cut out is formed, andthe cut-out part is a recessed part that is formed from a peripheral edge of the boss part toward a space between the two through-holes.2. (canceled)3. The aircraft component according to claim 1 , wherein the recessed part is formed into a semicircular shape in the outer peripheral surface.4. The aircraft component according to claim 1 , whereinone of the two through-holes is an aperture, and the other is a bolt-hole having an aperture area smaller than the aperture, anda radius of the recessed part is the same as a radius of the bolt-hole.5. An aircraft component used in a gas turbine engine for an aircraft claim 1 , the aircraft component comprising:an annular part having an outer peripheral surface; anda boss part protruding from the outer peripheral surface of the annular part in a radial direction, whereinin the boss part, at least two through-holes are formed to penetrate the boss part in the radial direction at predetermined intervals,in the boss part ...

TURBINE COWLING SYSTEM

A steam turbine cowling system is disclosed. The steam turbine cowling system including: a lower portion configured to be disposed proximate an inner casing of a steam turbine; and an upper portion connected to at least one of the lower portion and the inner casing, the upper portion shaped to be disposed proximate the inner casing of the steam turbine, the upper portion substantially defining a flowpath about the inner casing. 1. A steam turbine cowling system comprising:a lower portion configured to be disposed proximate an inner casing of a steam turbine; andan upper portion connected to at least one of the lower portion and the inner casing, the upper portion shaped to be disposed proximate the inner casing of the steam turbine and substantially defining a flowpath about the inner casing.2. The steam turbine cowling system of claim 1 , wherein at least one of the upper portion and the lower portion is configured as an insulator about the inner casing.3. The steam turbine cowling system of claim 1 , wherein the lower portion is permanently connected to the inner casing.4. The steam turbine cowling system of claim 1 , wherein the upper portion is connected to at least one of the inner casing or a steam guide in the steam turbine.5. The steam turbine cowling system of claim 4 , wherein the upper portion is releasably coupled to the inner casing.6. The steam turbine cowling system of claim 1 , wherein the at least one of the upper portion and the lower portion include a substantially smooth radially inward facing surfaces.7. The steam turbine cowling system of claim 1 , wherein the upper portion includes a steam inlet.8. The steam turbine cowling system of claim 1 , wherein the upper portion is configured to guide a flow toward the lower portion.9. The steam turbine cowling system of claim 1 , wherein the upper portion and the lower portion substantially enclose the inner casing and define a flowpath from a top of the inner casing to a condenser.10. The steam ...

SYSTEM FOR FAULT TOLERANT PASSAGE ARRANGEMENTS FOR HEAT EXCHANGER APPLICATIONS

The heat exchanger assembly includes a heat exchanger body and a plurality of columns of fluid passages arranged in a first direction within the heat exchanger body. The plurality of columns of fluid passages includes at least one first fluid column of fluid passages and at least two second fluid columns of fluid passages. The first fluid column is interspersed between two second fluid columns. The first fluid column includes a plurality of first fluid passages configured to channel a first fluid through the heat exchanger body. The at least two second fluid columns includes a plurality of second fluid passages configured to channel a second fluid through the heat exchanger body. The plurality of first fluid passages is offset with respect to the plurality of second fluid passages. 1. A heat exchanger assembly configured to transfer heat between a first fluid and a second fluid , said heat exchanger assembly comprising:a heat exchanger body; anda plurality of columns of fluid passages arranged in a first direction within said heat exchanger body, said plurality of columns of fluid passages comprising at least one first fluid column of fluid passages and at least two second fluid columns of fluid passages, said first fluid column interspersed between two second fluid columns;wherein said at least one first fluid column comprises a plurality of first fluid passages configured to channel a first fluid through said heat exchanger body; andwherein said at least two second fluid columns comprises a plurality of second fluid passages configured to channel a second fluid through said heat exchanger body, said plurality of first fluid passages offset with respect to said plurality of second fluid passages.2. The heat exchanger assembly of claim 1 , wherein said plurality of first fluid passages and said plurality of second fluid passages each comprising an elliptical cross-section fluid passage.3. The heat exchanger assembly of claim 1 , wherein said plurality of first fluid ...

INNER CASING FOR STEAM TURBINE ENGINE

A system includes a steam turbine. The steam turbine includes an outer casing and an inner casing disposed within the outer casing. The inner casing is horizontally split in an axial direction into an upper inner casing portion and a lower inner casing portion. The steam turbine also includes an impulse stage disposed within the inner casing, wherein the inner casing is configured to provide full arc admission of a fluid to the impulse stage. The steam turbine further includes at least one reaction stage having multiple blades. The at least one reaction stage is integrated within the inner casing. 1. A steam turbine , comprising:an outer casing;an inner casing disposed within the outer casing, wherein the inner casing is horizontally split in an axial direction into an upper inner casing portion and a lower inner casing portion, wherein the inner casing includes a retainer that interfaces with a portion of the outer casing to block movement of the inner casing relative to the outer casing in response to an axial force generated during operation of the steam turbine, and wherein the inner casing includes a flange comprising an upper flange portion and a lower flange portion; andat least one steam duct comprising an upper stream duct portion disposed in the upper inner casing portion and a lower steam duct portion disposed in the lower inner casing portion, the at least one steam duct configured to form a sealed interface between the upper and lower flange portions to block leakage of fluid through the sealed interface, the sealed interface comprising an annular seal ring and an anti-rotation mechanism disposed through a portion of the annular seal ring to block rotation of the annular seal ring relative to the upper and lower steam duct portions.2. The steam turbine of claim 1 , further comprising at least one reaction stage comprising a plurality of blades integrated within the inner casing.3. The steam turbine of claim 2 , further comprising at least one impulse ...

ATTACHMENT OF A NOZZLE TO A CASING OF A TURBOMACHINE

The invention relates to an assembly comprising a turbomachine casing () and a nozzle made of ceramic matrix composite material having a blade (), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part () of the nozzle to the casing (), said connecting part () extending substantially radially outwards, the blade () and said connecting part () being formed in one piece, said assembly being characterized in that the connecting part () is fastened to a first radial wall () integral with the casing () by fastening means (). 171212931173121313151753. An assembly comprising a turbomachine casing () and a nozzle () made of ceramic matrix composite material having a blade () , the frontside and backside surfaces of which delimit an internal cavity () , and which is connected at its radially external end by a connecting part () of the nozzle () to the casing () , said connecting part () extending substantially radially outwards , the blade () and said connecting part () being formed in one piece , said assembly being characterized in that the connecting part () is fastened to a first radial wall () integral with the casing () by fastening means ().2314951. An assembly according to claim 1 , characterized in that the radially external end of said connecting part () comprises at least one radial flange () claim 1 , extending strictly radially and being applied in the circumferential direction to said first radial wall ().38117818385834931. An assembly according to claim 2 , characterized in that it comprises an intermediate part () for fastening the nozzle () to the casing () claim 2 , the intermediate part () comprising a circumferential wall () and said at least one first radial wall () which extends radially inward from said circumferential wall () and is fastened to said at least one radial flange () of the connecting part ().4117965676567535131. An assembly according to claim 1 , ...

Casing Having a Non-Axisymmetric Composite Wall

Walls of gas turbine engine casings, fan cases, and methods for forming walls, e.g., fan case walls, are provided. For example, a wall comprises a plurality of composite plies arranged in a ply layup. The wall is annular and circumferentially segmented into a plurality of regions that include at least one first region and at least one second region. The ply layup in the first and second regions is different such that the ply layup is non-axisymmetric. An exemplary fan case comprises an annular inner shell, a filler layer, an annular back sheet, and an annular outer layer. The back sheet is circumferentially segmented into a plurality of regions, including at least one first region and at least one second region, and comprises a plurality of composite plies arranged in a ply layup that is different in the first and second regions such that the ply layup is non-axisymmetric. 1. A wall of a gas turbine engine casing , comprising:a plurality of composite plies arranged in a ply layup,wherein the wall is annular and is circumferentially segmented into a plurality of regions, the plurality of regions including at least one first region and at least one second region, andwherein the ply layup in the at least one first region is different from the ply layup in the at least one second region such that the ply layup is non-axisymmetric.2. The wall of claim 1 , wherein the ply layup in the at least one first region is formed from a first plurality of plies claim 1 ,wherein the first plurality of plies comprises fibers oriented in a first direction and fibers oriented in a second direction.3. The wall of claim 2 , wherein the ply layup in the at least one second region is formed from the first plurality of plies and a second plurality of plies claim 2 ,wherein the second plurality of plies comprises fibers oriented in a third direction and fibers oriented in a fourth direction, the third and fourth directions being different from the first and second directions.4. The wall of ...

GAS TURBINE AND GAS TURBINE MANUFACTURING METHOD

According to an embodiment, a gas turbine includes: a casing; a rotor shaft penetrating through the casing; a plurality of turbine stages which are in the casing and are arranged along an axial direction of the rotor shaft and through which a working fluid passes; two bearings disposed on outer sides of the casing in terms of the axial direction and supporting the rotor shaft in a rotatable manner; and a plurality of outlet pipes through which the working fluid having finished work in the turbine stages is discharged. The outlet pipes are provided in an upper half and a lower half of the casing.

Assembly or Disassembly Method for Steam Turbine Casing

An assembly or disassembly method for a casing of a steam turbine in which an inner casing is installed in an outer casing, and the inner casing and the outer casing are fixed at a fixing position, wherein when the inner casing is assembled or disassembled in a state where the fixing position and a gravity center of the inner casing are at different positions in an axial direction of the inner casing, a tilt adjusting jig is interposed between the outer casing and the inner casing so that the assembly or disassembly of the casing is performed while maintaining a tilt of the inner casing with the tilt adjusting jig.

GAS TURBINE ENGINE ATTACHMENT STRUCTURE AND METHOD THEREFOR

A method of assembling an attachment structure of a gas turbine engine includes providing a frame that has a first annular case, an inner annular case spaced radially inwardly from the first annular case, and a plurality of vanes extending between the inner case and the first annular case, providing a second annular case that extends around the frame, the first annular case and the second annular case include a plurality of interlocks, each of the plurality of interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second annular case, and inserting the first member in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case. 1. A method of assembling an attachment structure of a gas turbine engine , the method comprising:providing a frame including a first annular case, an inner annular case spaced radially inwardly from the first annular case, and a plurality of vanes extending between the inner case and the first annular case;providing a second annular case extending around the frame, the first annular case and the second annular case including a plurality of interlocks, each of the plurality of interlocks including a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second annular case; andinserting the first member in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.2. The method as recited in claim 1 , wherein the plurality of interlocks permits relative radial movement between the first annular case and the second annular case.3. The method as recited in claim 1 , further including ...

STEAM TURBINE AND METHOD OF MANUFACTURING STEAM TURBINE

A steam turbine includes a casing which is dividable and of which both ends are open, and a bundle accommodated in the casing. The bundle includes a rotor, a plurality of diaphragms which can be divided, a bundle casing to which the diaphragm is fixed inside thereof, and a bearing portion fixed to an inside of the bundle casing on an outside of the diaphragm, and a seal portion fixed to the inside of the bundle casing between the diaphragm and the bearing portion. The bundle casing can be attached and detached to and from the casing in a state of holding the rotor, the diaphragm, the bearing portion, and the seal portion. 1. A steam turbine comprising:a casing which is divided into an upper half casing on an upper side in a vertical direction and a lower half casing on a lower side in the vertical direction by a dividing surface, and which has a cylindrical shape open at both ends; anda bundle which is accommodated in the casing such that both ends thereof protrude from an opening of the casing, a rotor rotatable centering on an axis,', 'a plurality of diaphragms which have a ring shape covering the rotor from an outside in a radial direction relative to the axis, and are divided into upper half diaphragms on the upper side in the vertical direction and lower half diaphragms on the lower side in the vertical direction by a dividing surface,', 'a bundle casing which has a cylindrical shape covering the rotor and the plurality of the diaphragms from the outside in the radial direction, and to which the plurality of the diaphragms are fixed inside thereof,', 'a bearing portion which is fixed to an inside of the bundle casing on an outside of the plurality of the diaphragms in the axial direction in which the axis extends, and rotatably supports the rotor, and', 'a seal portion which is fixed to the inside of the bundle casing between the plurality of the diaphragms and the bearing portion in the axial direction, and seals between an outer peripheral surface of the ...

Combustor heat shield and method of cooling same

A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.

Gas turbine subassembly

The present invention relates to a subassembly for a gas turbine, in particular a gas turbine aircraft engine, having a turbine casing ( 11 ); a midframe ( 14 ), which is adjacent downstream to the turbine casing and has a number of support ribs ( 15 ) spaced apart in the peripheral direction. The turbine casing and the midframe define a flow duct ( 33 ) for a working gas exiting a combustion chamber of the gas turbine, and a cavity, in particular a cooling air duct ( 19 ), with an opening on the flow duct side is formed between the turbine casing and the midframe. An edge contour ( 40 ) of the opening on the turbine casing side varies along the periphery radially and/or axially.

TURBINE CASING WITH SERVICE WEDGE

A turbine casing is provided and includes first and second turbine casing shells configured to be removably coupled to one another. At least one of the first and second turbine casing shells is formed to define an access slot. At least one service wedge is configured to be removably installed in the access slot. 1. A turbine casing , comprising:first and second turbine casing shells configured to be removably coupled to one another,at least one of the first and second turbine casing shells being formed to define an access slot; andat least one service wedge configured to be removably installed in the access slot.2. The turbine casing according to claim 1 , wherein the first turbine casing shell comprises a lower hemispherical casing and the second turbine casing shell comprises an upper hemispherical casing and is formed to define the access slot.3. The turbine casing according to claim 1 , wherein the access slot is defined along a centerline of the at least one of the first and second turbine casing shells.4. The turbine casing according to claim 1 , wherein a position of the access slot is defined such that the access slot is offset from a centerline of the at least one of the first and second turbine casing shells.5. The turbine casing according to claim 1 , wherein the at least one of the first and second turbine casing shells is formed to define multiple access slots and the at least one service wedge comprises multiple service wedges claim 1 , each one of the multiple service wedges being configured to be removably installed in a corresponding one of the multiple access slots.6. The turbine casing according to claim 5 , wherein the multiple access slots are arranged symmetrically relative to a centerline of the at least one of the first and second turbine casing shells.7. The turbine casing according to claim 1 , wherein the access slot is elongate in an axial dimension of at least one of the first and second turbine casing shells.8. The turbine casing ...

SEGMENTED CONDUIT WITH AIRFOIL GEOMETRY

A conduit that includes a first segment forming a first sidewall of the conduit and a second segment forming a second sidewall of the conduit. The first segment may include a first inner surface and a first outer surface and the second segment may include a second inner surface and a second outer surface. The first segment may be coupled to the second segment such that the first inner surface and the second inner surface jointly form an inner conduit surface and the first outer surface and the first inner surface jointly form at least a portion of an outer conduit surface, wherein the outer conduit surface has an airfoil geometry. The first segment and the second segment may be detachably coupled together. 1. A conduit comprising:a first segment forming a first sidewall of the conduit, the first segment comprising a first inner surface and a first outer surface; anda second segment forming a second sidewall of the conduit, the second segment comprising a second inner surface and a second outer surface;wherein the first segment is coupled to the second segment such that the first inner surface and the second inner surface jointly form an inner conduit surface and the first outer surface and the first inner surface jointly form at least a portion of an outer conduit surface, wherein the outer conduit surface has an airfoil geometry.2. The conduit of claim 1 , wherein the first segment and the second segment are detachably coupled together.3. The conduit of claim 1 , wherein the first outer surface at least partially forms one of an upper surface and a lower surface of the airfoil geometry of the outer conduit surface and the second outer surface at least partially forms the other of the upper surface and the lower surface of the airfoil geometry of the outer conduit surface.4. The conduit of claim 3 , further comprising a third segment and a fourth segment claim 3 , wherein the third segment couples the first segment to the second segment and forms a leading edge ...

TURBOMACHINE COMPRISING A PLURALITY OF FIXED RADIAL BLADES MOUNTED UPSTREAM OF THE FAN

Bypass turbine engine, in particular for an aircraft, in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising: 25242530245. Turbine engine according to claim 1 , wherein the means for individually adjusting the pitch of the radial vanes () comprise a single control ring () and rods ( claim 1 , ) for connecting said control ring () to each of said radial vanes ().311121311. Turbine engine according to claim 1 , wherein the inner casing () claim 1 , the inter-duct casing () and the outer casing () are at a radial distance from one another in the turbine engine () so as to define a turbine engine () having a bypass ratio (BPR) that is greater than or equal to 15.4202. Turbine engine according to claim 1 , wherein the rotational speed of the free ends of the blades () of the movable fan () is less than 340 m/s.551. Turbine engine according to claim 1 , wherein the plurality of variable-pitch radial vanes () extend in the same plane which is transverse to the axis of the turbine engine ().6525. Turbine engine according to claim 1 , wherein the axial distance between the plurality of variable-pitch radial vanes () and the movable fan () is between 0.1 and 10 times the mean chord of a variable-pitch radial vane ().720211131. Turbine engine according to claim 1 , wherein the blades () of the movable fan () extend between the inner casing () and the outer casing () of the turbine engine ().85. Turbine engine according to claim 1 , wherein each variable-pitch radial vane () has an aerodynamic profile so as to accelerate the incident air flow in accordance with a laminar flow.95. Turbine engine according to claim 1 , wherein each variable-pitch radial vane () has a body which is movable in rotation about a radial axis.1055051. Turbine engine according to claim 1 , wherein each variable-pitch radial vane (′) has a fixed body (′) and a movable flap (′).115. Turbine engine according to claim 1 , wherein each variable-pitch ...

Turbine housing

A turbine housing includes an inner pipe that forms an exhaust air flow path in which a turbine wheel accommodating a turbine shaft is arranged; and an outer pipe that is spaced from the inner pipe at a predetermined distance and covers the inner pipe. At least one reinforcing plate is secured to an inner surface of the outer pipe.

Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device

Combustor device having a twin-shell tubular casing including: an inner tubular member which extends roughly coaxial a longitudinal axis of the combustor device, delimits the combustion chamber and surrounds the burner; and an outer tubular housing which extends roughly coaxial outside of the inner tubular member. An intermediate supporting structure includes an outer annular supporting member, an inner annular supporting member, and a series of three or more oblong connecting beams angularly staggered about the longitudinal axis of combustor device in cantilever manner to stably connect the inner and outer annular supporting members.

ROTARY MACHINE

A rotary machine includes: a rotary shaft supported by a bearing provided on a bearing base; and a casing housing the rotary shaft at least in part. The casing includes at least one support leg configured to support the casing on a base plate of a support structure member, and a support leg of the at least one support leg is supported on a support leg base provided on the base plate. The rotary machine further includes a height adjustment mechanism configured to adjust height of the casing, and the height adjustment mechanism includes an inclined surface of a support leg formed on the support leg, an inclined surface of a support leg base formed on the support leg base while facing the inclined surface of the support leg, and an actuator configured to move the support leg and the support leg base relative to each other. 1. A rotary machine comprising:a rotary shaft supported by a bearing provided on a bearing base; anda casing housing the rotary shaft at least in part,wherein, the casing includes at least one support leg configured to support the casing, and a support leg of the at least one support leg is supported by a support leg base,the rotary machine further includes a height adjustment mechanism configured to adjust height of the casing, andthe height adjustment mechanism includesan inclined surface of a support leg formed on the support leg;an inclined surface of a support leg base formed on the support leg base while facing the inclined surface of the support leg; andan actuator configured to move the support leg and the support leg base relative to each other.2. The rotary machine according to claim 1 ,wherein a rail configured to define a direction of movement of the support leg base is provided.3. The rotary machine according to claim 1 ,wherein at least two of the support legs are provided in the casing, andthe at least two of the support legs are disposed with inclination directions of inclined surfaces of the at least two of support legs being in line ...

STEAM TURBINE INNER CASING WITH MODULAR INSERTS

The embodiments relate to a steam turbine with modular inserts that are removably insertable into an inner case. The modular inserts include a seal carrier modular insert located towards a first end of the steam turbine, for carrier seals located between the inner casing the rotor, that is cylindrically shaped and removably insertable into the inner casing, an inlet spiral insert, adjacent the seal carrier modular insert and removably insertable into the inner casing, for introducing steam into the steam expansion flow path so as to circumferentially distribute steam feed into the steam turbine; and a blade carrier modular insert, adjacent the inlet spiral insert, that is also cylindrically shaped and removably insertable into the inner casing, for retaining stationary blades. 1. A steam turbine arrangement comprising:an outer casing defining an outer limit of the steam turbine;an inner case, encased by the outer casing, configured and arranged to form a steam expansion flow path in which work is generated by turbine stages located within the inner case;a rotor, concentric to and contained at least partially within both the inner casing and the outer casing;a seal carrier modular insert, towards a first end of the steam turbine, for carrying seals located between the inner casing the rotor, that is cylindrically shaped and removably insertable into the inner casing;an inlet spiral insert, adjacent the seal carrier modular insert and removably insertable into the inner casing, for introducing steam into the steam expansion flow path so as to circumferentially distribute steam feed into the steam turbine; anda blade carrier modular insert, adjacent the inlet spiral insert, that is cylindrically shaped and removably insertable into the inner casing, for retaining stationary blades.2. The steam turbine of claim 1 , wherein the inner casing and the seal carrier modular insert complementarily comprise a first slot and a first key configured to prevent rotation of the seal ...

DUAL-WALLED COMPONENTS FOR A GAS TURBINE ENGINE

Techniques for forming a dual-walled component for a gas turbine engine that include chemically etching at least one of a hot section part or a cold section part to form an etched part having plurality of support structures and bonding the etched part to a corresponding cold section part or a corresponding hot section part to form a dual-walled component, with the plurality of support structures defining at least one cooling channel between the at least one of the hot section part or the cold section part and the corresponding cold section part or the corresponding hot section part. 1. A method for forming a dual-walled component for a gas turbine engine , the method comprising:chemically etching at least one of a hot section part or a cold section part to form an etched part having plurality of support structures; andbonding the etched part to a corresponding cold section part or a corresponding hot section part to form a dual-walled component, wherein the plurality of support structures define at least one cooling channel between the at least one of the hot section part or the cold section part and the corresponding cold section part or the corresponding hot section part.2. The method of claim 1 , further comprising:prior to chemically etching the at least one hot section part or cold section part, applying a mask to a surface of the at least one hot section part or cold section part to define a cooling channel pattern on the surface of the at least one hot section part or cold section part; andafter chemically etching the at least one hot section part or cold section part, removing the mask.3. The method of claim 2 , wherein the mask is applied to a concave surface of the at least one hot section part or cold section part.4. The method of claim 1 , wherein the etched part comprises the hot section part.5. The method of claim 1 , wherein bonding the etched part to the corresponding cold section part or the corresponding hot section part comprises at least one of ...

Casing Of A Turbocharger And Turbocharger

A casing of a turbocharger, which surrounds the turbocharger radially and axially outside at least in sections. The casing has multiple casing modules including a temperature casing module that surrounds the turbine, the compressor, and/or the bearing housing radially outside and axially outside at least in sections, an inner burst protection casing module following the temperature casing module on the outside, and at least one outer burst protection casing module following the inner burst protection casing module on the outside, which surrounds the inner burst protection casing module. 1. A casing of a turbocharger , configured radially and axially surround , at least in sections , a turbine housing and/or a compressor housing and/or a bearing housing of the turbocharger , the casing comprising:at least one temperature casing module, which radially and axially surrounds, at least in sections, the turbine housing and/or the compressor housing and/or the bearing housing outside;an inner burst protection casing module following on an outside of the temperature casing module, which radially and axially surrounds, at least in sections, the temperature casing module; andat least one outer burst protection casing module following on an outside of the inner burst protection casing module, which exclusively radially surrounds, at least in sections, the inner burst protection casing module.2. The casing according to claim 1 , wherein the temperature casing module and the burst protection casing modules are circumferential in a circumferential direction.3. The casing according to claim 1 , further comprising:a flange connection casing module arranged between the temperature casing module and the turbine housing or the compressor housing, which surrounds the turbine housing or the compressor housing radially outside and axially outside exclusively in a region of a connecting flange of turbine housing or compressor housing.4. The casing according to claim 3 , wherein the ...

Forged cast forged outer case for a gas turbine engine

A case for a gas turbine engine includes a cast case section cast case section configured to be welded between a forward case section and an aft case section.

GAS TURBINE ENGINE SEALING ARRANGEMENT

A sealing arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a groove that extends between an upstream rail and a downstream rail, a complementary static structure spaced from the groove, and a seal positioned within the groove and configured to seal a clearance between at least one of the upstream rail and the downstream rail and the complementary static structure. 1. A static frame for a gas turbine engine , comprising:an annular platform, the platform having a first platform surface that faces radially toward a core flow path and includes a plurality of airfoils extending therefrom, and a second platform surface that faces radially away from the core flow path;a static structure disposed radially adjacent to the second platform surface, the static structure including a third platform surface that radially faces the second platform surface, wherein said static structure is a mid-turbine frame arranged between a first turbine and a second turbine; and a first annular rail extending radially from the second platform surface toward the third platform surface by a first distance;', 'a second annular rail that is axially spaced from the first annular rail, the second annular rail extending radially from the second platform surface towards the third platform surface by a second distance that is less than the first distance;', 'an annular groove on the second platform surface defined between the first annular rail and the second annular rail so that the annular groove is J-shaped; and', 'an annular seal extending from the third platform surface into the annular groove to form a sealing relationship between the annular seal and the second annular rail., 'a fluid seal between the second platform surface and the third platform surface, the fluid seal comprising2. The static frame as recited in claim 1 , wherein said groove and said seal are arranged at an inner diameter portion of the static frame.3. ...

NACELLE MOUNTED LATCHING SYSTEM

A nacelle for a gas turbine engine includes a bifurcation, an outer diameter cowl and a first latch system. The outer diameter cowl extends from the bifurcation and the first latch system is mounted on the outer diameter cowl. The first latch system is spaced along the outer diameter cowl from the bifurcation. 120-. (canceled)21. A nacelle for a gas turbine engine , the nacelle comprising:an upper bifurcation; anda lower bifurcation;an inner diameter cowl extending between the upper and lower bifurcations; anda first latch system mounted on the inner diameter cowl and spaced along the inner diameter cowl between the upper and lower bifurcations.22. The nacelle of claim 21 , further comprising a second latch system claim 21 , wherein the inner diameter cowl is separated into first and second halves claim 21 , and wherein the first latch system is mounted on the first half and the second latch system is mounted to the second half.23. The nacelle of claim 21 , further comprising:an diameter outer cowl.24. The nacelle of claim 21 , wherein the first latch system includes:a handle mounted within and pivotal to protrude from the inner diameter cowl;one or more linking members extending through the inner diameter cowl from the handles into the fan airflow; andone or more latching mechanisms disposed toward a forward end of the inner diameter cowl and connected to the one or more linking members.25. The nacelle of claim 24 , wherein the inner diameter cowl includes an aft core cowl and the handle is mounted on the aft core cowl.26. The nacelle of claim 24 , wherein the handle opens in a forward direction relative to the inner diameter cowl.27. The nacelle of claim 24 , wherein the latching mechanism comprise pin latches that engage the engine case.28. The nacelle of claim 24 , wherein the one or more linking members comprise push-pull cables.29. A nacelle for a gas turbine engine claim 24 , the nacelle comprising:a first door having a first inner diameter cowl connected to ...

STEAM TURBINE HOUSING

A steam turbine housing is provided having a housing wall and a stiffening cradle attached to the inner side which has two encircling inner webs which are arranged axially adjacent to one another and which project radially inward from the housing wall. Between the inner webs, running parallel and axially centrally, a central web is attached to the inner side of the housing wall, the radially inner edge of which is straight, wherein at the radially inner edge of the central web, the central web forks in a Y-shaped manner inward into two transition webs which extend to and merge into the adjacent inner web, such that the inner webs are fastened directly to the housing wall outside the circumferential extent of the transition webs and are fastened to the housing wall via the transition webs and the central web within the circumferential extent of the transition webs. 1. A steam turbine housing comprising:a housing wall, to the inside of which is attached a stiffening cradle having two circumferential inner webs arranged axially next to one another and projecting radially inward from the housing wall, a central web being attached to the inside of the housing wall between the inner webs so as to run parallel to these and axially centrally,the radially inner rim of the central web being straight so that the longitudinal ends of this rim meet the housing wall, defining the circumferential extent of the central web,wherein the central web forks, at its inner rim, in the shape of an inward-facing Y to form two transition webs which in each case extend as far as the adjacent inner web and merge into the latter,such that, outside the circumferential extent of the transition webs, the inner webs are attached to the housing wall directly, while inside the circumferential extent of the transition webs they are attached to the housing wall via the transition webs and the central web.2. The steam turbine housing as claimed in claim 1 ,wherein the inner rim of the central web has a ...

TURBINE STATOR, TURBINE, AND GAS TURBINE INCLUDING THE SAME

A turbine stator, into which combustion gas supplied from a combustor of a gas turbine flows, has an improved structure capable of preventing circumferential movement of turbine vanes. The turbine stator, which may be included in a turbine of a gas turbine having the improved structure, includes a casing including first and second casings constituting respective casing halves, the first and second casings having a fastening groove formed on at least one contact surface between the first casing and the second casing; a plurality of vane airfoils configured to be installed on an inner peripheral surface of the casing and arranged in a multi-stage manner in a flow direction of the combustion gas; and a stop configured to be fixed with respect to a vane airfoil of the plurality of vane airfoils and to be inserted into the fastening groove to fix the vane airfoil to the casing. 1. A turbine stator into which combustion gas supplied from a combustor flows , the turbine stator comprising:a casing including first and second casings constituting respective casing halves, the casing having a contact surface between the first and second casings, and a fastening groove formed on at least one contact surface of the first casings and the second casings;a plurality of vane airfoils configured to be installed on an inner peripheral surface of the casing and arranged in a multi-stage manner in a flow direction of the combustion gas; anda stop configured to be fixed with respect to a vane airfoil of the plurality of vane airfoils and to be inserted into the fastening groove to fix the vane airfoil to the casing.2. The turbine stator according to claim 1 , further comprising:a flange protruding radially outward from either end of an outer peripheral surface of the casing, for coupling together the first and second casings; anda first vane airfoil of the plurality of vane airfoils disposed on an inner peripheral surface of the casing corresponding to a position of the flange.3. The ...

GAS TURBINE

A gas turbine includes a housing; a rotor rotatable by a fluid flowing through the housing; a bearing for rotatably supporting the rotor; and a support structure configured to support the bearing with respect to the housing. The support structure includes an inner casing accommodating the bearing; an outer casing fastened to the housing; and a strut extending between the inner and outer casings, and at least one of the inner casing and the outer casing includes a diaphragm that is deformable in a radial direction of the rotor. Each casing includes a strut root connected to the strut, a strut platform surrounding the strut root and being formed as the diaphragm; and a main body surrounding the strut platform. Damage to the support structure due to thermal expansion can be prevented, and the support structure can be easily designed to avoid resonance between the support structure and the rotor. 1. A gas turbine comprising:a housing;a rotor rotatable by a fluid flowing through the housing;a bearing for rotatably supporting the rotor; and an inner casing accommodating the bearing;', 'an outer casing fastened to the housing; and', 'a strut extending between the inner and outer casings,', 'wherein at least one of the inner casing and the outer casing comprises a diaphragm that is deformable in a radial direction of the rotor., 'a support structure configured to support the bearing with respect to the housing, the support structure comprising2. The gas turbine according to claim 1 , wherein the inner casing comprises:an inner casing strut root connected to the strut;an inner casing strut platform surrounding the inner casing strut root and being formed as the diaphragm; andan inner casing main body surrounding the inner casing strut platform.3. The gas turbine according to claim 2 , wherein the inner casing strut platform has a thickness smaller than a thickness of the inner casing main body.4. The gas turbine according to claim 3 , wherein the thickness of the inner ...

TURBINE SUPPORT STRUCTURE, TURBINE AND GAS TURBINE USING THE SAME

A turbine support structure supports a turbine casing and is configured to be movable when the turbine casing is thermally deformed while a gas turbine is operated, thus preventing a fatigue fracture of the turbine casing from occurring. The turbine support structure includes a pair of supports, each having an upper and lower end, for supporting respective opposite side surfaces of the turbine casing at the upper end of either support; and a movable unit installed at the lower end of each support and configured to movably support the lower end of the support. The movable unit is spaced outwardly from the corresponding opposite side surface of the turbine casing, so that the corresponding support inclines toward the turbine casing and is rotatable. The lower end of each support is rotatably coupled to the corresponding movable unit so that the support is rotatable toward an axis of the turbine casing. 1. A turbine support structure for supporting a turbine casing of a gas turbine , the turbine support structure comprising:a pair of supports, each having an upper and lower end, for supporting respective opposite side surfaces of the turbine casing at the upper end of either support; anda movable unit installed at the lower end of each support and configured to movably support the lower end of the support.2. The turbine support structure according to claim 1 , wherein each movable unit is spaced outwardly from the corresponding opposite side surface of the turbine casing claim 1 , so that the corresponding support inclines toward the turbine casing.3. The turbine support structure according to claim 1 , further comprising:a pair of flange parts protruding outward from the respective opposite side surfaces of the turbine casing; anda bolt part formed on the upper end of each support and coupled to the corresponding flange part.4. The turbine support structure according to claim 3 , wherein each flange part has an insert hole for receiving the bolt part in order to ...

Casing for a gas turbine engine and a method of manufacturing such a casing

A gas turbine engine casing 2 comprising: an inner circumferential wall 12; an outer circumferential wall 14 spaced radially outwardly from the inner wall 12; wherein the inner and outer circumferential walls 12, 14 are formed by an axially repeating profile comprising an inner wall portion 6 and an outer wall portion 8 connected to one another by an intermediate portion 10, the axially repeating profile being arranged such that the inner wall portion 6 abuts against and is connected to an adjacent inner wall portion 6 to form the inner circumferential wall 12 and the outer wall portion 8 abuts against and is connected to an adjacent outer wall portion 8 to form the outer circumferential wall 14.

SPLIT CASE STRUCTURE FOR A GAS TURBINE ENGINE

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint.

GAS TURBINE

A gas turbine includes an outer casing having an annular shape; an inner casing disposed inside the outer casing; and a plurality of struts, each strut having a first end fixed to an outer surface of the inner casing, a second end fixed to an inner surface of the outer casing, and an inclined portion for guiding a flow of combustion gas, wherein the inclined portion is inclined from a front side to a rear side. 1. A gas turbine comprising:an outer casing having an annular shape;an inner casing disposed inside the outer casing; anda plurality of struts, each strut having a first end fixed to an outer surface of the inner casing, a second end fixed to an inner surface of the outer casing, and an inclined portion for guiding a flow of combustion gas,wherein the inclined portion is inclined toward a rear end from a front end of the strut.2. The gas turbine according to claim 1 , wherein the inclined portion is formed such that a tip of the strut is inclined toward a trailing end from a leading end thereof.3. The gas turbine according to claim 1 , wherein the inclined portions of the struts all have the same inclination angle.4. The gas turbine according to claim 1 , wherein the inclined portions of the struts have different inclination angles.574. The gas turbine according to claim 1 , wherein the inclined portion of each of the struts has an inclination angle corresponding to an inclination angle of an inclined portion of a blade extending obliquely toward a trailing end from a leading end of a tip of a last blade positioned in front of the strut.6. The gas turbine according to claim 1 , wherein the inner surface of the outer casing is inclined with the same slope as the inclined portion of the strut.7. The gas turbine according to claim 1 , wherein the inclination angle of each of the inclined portions is an angle within a range of 5° to 30°.8. The gas turbine according to claim 1 , wherein the strut includes a gas contact surface extending from a leading edge to a ...

CASING POSITION ADJUSTMENT DEVICE

In a steam turbine including a rotor including a free side end fixed by a journal bearing (not illustrated) in a radial direction and a fixed side end fixed by a thrust bearing in an axial direction, and a casing including a fixed side end fixed by the thrust bearing in the axial direction (rotor axial direction), a casing position adjustment device is configured to adjust an axial position of the casing with respect to the rotor due to thermal expansion. The casing position adjustment device includes: a low-pressure casing end plate, which is an end plate oriented to a free side in the axial direction in a low-pressure casing of the casing, and has a diaphragm shape deformable in the axial direction; and actuators, which deform the low-pressure casing end plate so that the low-pressure casing end plate extends toward the free side in the axial direction. 115-. (canceled)16. A casing position adjustment device in a steam turbine including a rotor including a free side end fixed by a journal bearing in a radial direction and a fixed side end fixed by a thrust bearing in an axial direction , and a casing including a fixed side end fixed by the thrust bearing in the axial direction , the casing position adjustment device configured to adjust an axial position of the casing with respect to the rotor due to thermal expansion , the casing position adjustment device comprising:a low-pressure casing end plate, which is an end plate oriented to a free side in the axial direction in a low-pressure casing of the casing, and has a diaphragm shape deformable in the axial direction; andactuators, which deform the low-pressure casing end plate such that the low-pressure casing end plate extends toward the free side in the axial direction.17. A casing position adjustment device according to claim 16 , wherein the casing is fixed by anchor bolts on the fixed side in the axial direction with respect to the low-pressure casing end plate.18. A casing position adjustment device ...

Turbomachine

A turbocharger includes a turbine with a housing and a rotor for expanding a first medium; a compressor with a housing and a rotor for compressing a second medium utilizing energy extracted in the turbine during expansion of the first medium. A housing surrounds the turbine housing and/or the compressor housing and/or the bearing housing at least in sections, which housing is at least formed from a first housing section and a second housing section, which are connected to one another via screw connections. On the first housing section, shearing force absorption elements are formed or fastened which extend through the second housing section and in the event that shearing forces occur, absorb the shearing forces and thus relieve the screw connections of the shearing forces. 1. A turbocharger comprising:a turbine for expanding a first medium, wherein the turbine comprises a turbine housing and a turbine rotor;a compressor for compressing a second medium utilizing energy extracted in the turbine during expansion of the first medium, wherein the compressor comprises a compressor housing and a compressor rotor coupled to the turbine rotor via a shaft;wherein the turbine housing and the compressor housing are each connected to a bearing housing arranged between the compressor housing and the turbine housing; the shaft being mounted in the bearing housing;a housing at least in sections surrounding the turbine housing and/or the compressor housing and/or the bearing housing, the housing at least formed from a first housing section and a second housing section connected to one another;screw connections for connecting the at least first and second housing sections; andshearing force absorption elements formed or fastened on the first housing section and extending through the second housing section, the shearing force absorption elements constructed and disposed to absorb the shearing forces in the event of shearing forces occurring and to relieve the screw connections of the ...

SEAL RETAINING ASSEMBLY

A seal retaining assembly includes a first segment coupled to a first structure. Also included is a recess of the first segment, the recess defined by a first and second wall, the first wall defining a first wall aperture, the second wall defining a second wall aperture. Further included is a second segment having a tab disposed within the recess in fitted contact with the first and second wall to retain the second segment to the first segment in a radial direction, the tab defining a tab aperture, the first and second segment defining an axial gap therebetween, the first wall aperture, the second wall aperture and the tab aperture are aligned to form a passage. Yet further included is a flex seal within the axial gap. Also included is a pin in the passage to fix the second segment to the first segment in axial and circumferential directions. 1. A seal retaining assembly comprising:a first segment operatively coupled to a first structure;a recess of the first segment, the recess defined by a first wall and a second wall, the first wall defining a first wall aperture, the second wall defining a second wall aperture;a second segment having a tab disposed within the recess in fitted contact with the first wall and the second wall to retain the second segment to the first segment in a radial direction, the tab defining a tab aperture, the first segment and the second segment defining an axial gap therebetween, the first wall aperture, the second wall aperture and the tab aperture are aligned to form a passage;a flex seal disposed within the axial gap; anda pin disposed in the passage to fix the second segment to the first segment in an axial direction and in a circumferential direction.2. The seal retaining assembly of claim 1 , wherein the first segment extends circumferentially around an axis.3. The seal retaining assembly of claim 1 , wherein the first segment comprises a plurality of circumferential segments each extending around a portion of a circumference of the ...

SHEET METAL TURBINE HOUSING WITH CELLULAR STRUCTURE REINFORCEMENT

Systems are provided for a reinforcement element coupled to a sheet metal turbine housing that imparts desirable thermal-protective and structurally strengthening characteristics to the housing layers. In one example, a system may include a turbine comprising a housing surrounding a turbine rotor, the housing having an outer layer surrounding an inner layer at a distance to form an intermediate space between the inner and outer layers. Moreover, disposed in the intermediate space is a reinforcement element coupled to the inner and outer layers, providing strength and consistent rigidity without a significant increase in weight to the housing. 1. A turbine comprising: an inner layer;', 'an outer layer, the outer layer surrounding the inner layer at a distance to form an intermediate space between the inner and outer layers; and', 'a reinforcement element disposed within the intermediate space and coupled to at least one of the inner layer and outer layer maintaining a threshold length between the inner layer and the rotor., 'a housing surrounding a rotor, the housing having2. The turbine of claim 1 , wherein the reinforcement element comprises a body of corrugated or bellowed layers of a sheet metal forming a pattern.3. The turbine of claim 2 , wherein the pattern is a honeycomb-like shape such that the cross-section of the reinforcement element is a plurality of hexagons.4. The turbine of claim 2 , wherein the pattern is a bellowing wave claim 2 , such that the cross-section of the reinforcement element is a sine wave.5. The turbine of claim 2 , wherein the pattern is a plurality of squares or triangles aligned in series.6. The turbine of claim 1 , wherein the reinforcement element is in face-sharing contact with a first surface of the outer layer facing toward the turbine rotor and a second surface of the inner layer facing away from the turbine rotor.7. The turbine of claim 1 , wherein the reinforcement element is coupled to one or more of the inner layer and ...

POWER TURBINE INLET DUCT LIP

A power turbine section for a gas turbine engine includes an inlet duct upstream of a first power turbine vane array, the inlet duct including a lip. 1. A power turbine section for a gas turbine engine comprising:a first power turbine vane array; andan inlet duct upstream of said first power turbine vane array, said inlet duct including an annular inner duct wall spaced from an annular outer duct wall, said annular inner duct wall including a lip.2. The power turbine section as recited in claim 1 , wherein said lip extends from a gas path surface of said annular inner duct wall.3. The power turbine section as recited in claim 1 , wherein said lip defines a ramp.4. The power turbine section as recited in claim 3 , wherein said ramp defines an angle of about ten (10) degrees with respect to a gas path surface.5. The power turbine section as recited in claim 1 , wherein said lip defines a downstream edge of said annular inner duct wall.6. The power turbine section as recited in claim 5 , wherein said downstream edge of said annular inner duct wall at least partially axially overlaps a mount lug of said first power turbine vane array claim 5 , said mount lug receivable into a bearing support.7. The power turbine section as recited in claim 1 , wherein said inlet duct generally forms a frustoconical shape.8. The power turbine section as recited in claim 7 , wherein an upstream edge of said annular inner duct wall and said annular outer duct wall are radially inboard of a respective downstream edge of said annular inner duct wall and said annular outer duct wall.9. The power turbine section as recited in claim 1 , further comprising an inlet case that supports said first power turbine vane array and said inlet duct upstream.10. The power turbine section as recited in claim 9 , further comprising an air strut that extends through said inlet case and said inlet duct.11. The power turbine section as recited in claim 10 , wherein said air strut extends through said inlet duct ...

Containment Case Having Ceramic Coated Fibers

Containment assemblies and methods for forming containment assemblies of gas turbine engines are provided. For example, a containment assembly comprises a containment case including a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. As another example, a containment assembly comprises an inner case and a containment case comprising a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. The containment case includes a greater proportion of the coated fibers at an inner surface of a layer of the containment case than at a location within the containment case that is radially outward from the inner surface. Methods for forming a containment assembly of a gas turbine engine are provided.

RADIALLY FASTENED FIXED-VARIABLE VANE SYSTEM

A split case assembly for a gas turbine engine includes an outer diameter case defining a partial case structure for a gas turbine engine and multiple fixed-variable vanes attached to an inner diameter surface of the outer diameter case. Each of the fixed-variable vanes protrudes radially inward from the outer diameter case. Each of the fixed-variable vanes in the plurality of fixed-variable vanes is interfaced with one of a plurality of inner diameter boxes at a radially inward end of the fixed-variable vane, such that the inner diameter boxes define an inner diameter of a flow path and the outer diameter case defines an outer diameter flow path. Each of the fixed-variable vanes are interfaced with the one of the plurality of inner diameter boxes through at least one inner diameter shoe in a plurality of inner diameter shoes. 1. A gas turbine engine comprising:a compressor section;a combustor section fluidly connected to the compressor section by a flow path;a turbine section fluidly connected to the combustor section by the flow path; a plurality of fixed vanes disposed circumferentially about, and radially spanning, said flow path;', 'a plurality of variable vanes, aft of said plurality of fixed vanes, wherein said plurality of variable vanes comprise at least a blade and a button, and wherein said plurality of variable vanes are disposed circumferentially about and radially spanning said flow path;', 'a plurality of inner diameter boxes radially inward of said plurality of fixed vanes and said plurality of variable vanes, each inner diameter box in said plurality of inner diameter boxes including at least one inner diameter box clearance hole receiving a connection feature of at least one corresponding fixed vane,', 'a plurality of inner diameter shoes disposed radially between said plurality of inner diameter boxes and said plurality of fixed vanes and said plurality of variable vanes, each of the inner diameter shoes including at least one inner diameter shoe ...

FASTENER ASSEMBLY FOR SECURING A TURBOMACHINE CASING AND METHOD FOR SECURING THE CASING

A casing including: a first casing section and a second casing section configured to be joined to the first casing section to form the casing; a first hole extending through a portion of the first casing section; a second hole extending through a portion of the second casing section, wherein the first and second holes are configured to be in alignment while the first and second casing sections are joined; a bushing seated in the second hole; a fastener having a shaft configured to extend through the first hole, extend into the second hole, and seat in and engage the bushing, wherein a thermal expansion coefficient of the bushing is greater than a thermal expansion coefficient of the shaft of the fastener, and the thermal expansion coefficient of the fastener is greater than a thermal expansion coefficients for each of the first and second casing sections. 1. A casing comprising:a first casing section and a second casing section configured to be joined to the first casing section to form the casing;a first hole extending through a portion of the first casing section;a second hole extending through a portion of the second casing section, wherein the first and second holes are configured to be in alignment while the first and second casing sections are joined;a bushing seated in the second hole;a fastener having a shaft configured to extend through the first hole, extend into the second hole, and seat in and engage the bushing,wherein a thermal expansion coefficient of the bushing is greater than a thermal expansion coefficient of the shaft of the fastener, and the thermal expansion coefficient of the fastener is greater than the thermal expansion coefficients for each of the first and second casing sections.2. The casing of wherein the bushing has a threaded outer surface at a first end region of the bushing and a threaded inner surface at a second end region claim 1 , which is opposite to the first end region.3. The casing of wherein the threaded outer surface of the ...

HEATSHIELD ASSEMBLY WITH DOUBLE LAP JOINT FOR A GAS TURBINE ENGINE

A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment. 1. A heat shield assembly for a gas turbine engine , the assembly comprising:a first heat shield segment defined about an axis;a second heat shield segment defined about said axis; anda double circumferential lap joint between said first heat shield segment and said second heat shield segment.2. The assembly as recited in claim 1 , whereinsaid double circumferential lap joint is defined by an outer cover and an alignment tab mounted to said first heat shield segment; andsaid outer cover and said alignment tab extend beyond an edge of said first heat shield segment.3. The assembly as recited in claim 2 , wherein said outer cover and said alignment tab form an interference fit with said second heat shield segment.4. The assembly as recited in claim 2 , wherein said outer cover includes a radiused end.5. The assembly as recited in claim 2 , wherein said alignment tab is a plate.6. The assembly as recited in claim 2 , wherein said alignment tab includes a curved end which curves away from said outer cover.7. The assembly as recited in claim 2 , wherein said outer cover is generally L-shaped in cross-section.8. The assembly as recited in claim 7 , wherein said outer cover includes an axial end radially displaced from said first heat shield segment.9. The assembly as recited in claim 8 , wherein said axial end includes a curved end that curves away from said first heat shield segment.10. The assembly as recited in claim 2 , wherein said outer cover is generally serpentine shaped.11. A case assembly for a gas turbine engine claim 2 , the assembly comprising:an outer air seal flange interface defined about an engine axis;a first heat shield segment defined about said axis radially outboard of ...

METHOD FOR DIVERTING FLOW AROUND AN OBSTRUCTION IN AN INTERNAL COOLING CIRCUIT

A rotary machine including: a casing providing an annular chamber for rotating components of the machine; a cooling passage extending through the casing or mounted to a surface of casing; a plug assembly connected to the cooling passage and in the casing or mounted to the casing, wherein the plug assembly includes a collar and a conduit aligned with an axis of the collar, and the collar includes a cooling air by-pass passage in fluid communication with the cooling passage such that cooling air from the cooling passage flows through the by-pass passage and returns to the cooling passage, and another cooling passage or a port extending through the conduit of the plug assembly. 1. A rotary machine comprising:a casing providing an annular chamber for rotating components of the machine;a cooling passage extending laterally through the casing or mounted to a surface of casing;a plug assembly connected to the cooling passage and in the casing or mounted to the casing, wherein the plug assembly includes a collar and a conduit extending through the collar, and the collar includes a cooling air by-pass passage in fluid communication with the cooling passage such that cooling air from the cooling passage flows through the by-pass passage and returns to the cooling passage, andanother cooling passage or a port extending through the conduit of the plug assembly.2. The rotary machine of wherein the conduit includes a hollow plug comprising an outer plug and an inner plug claim 1 , wherein the outer plug fits into an opening in the inner plug claim 1 , and the outer plug includes a flange seated on an outer surface of the inner shell and the inner plug includes a flange seated on an inner surface of the casing.3. The rotary machine of wherein the outer plug includes a ring slot in an outer sidewall claim 2 , and the inner plug includes a lip on an inner wall claim 2 , wherein the lip engages the ring slot while the outer plug and inner plug are joined together.4. The rotary ...

INNER CASING FOR STEAM TURBINE ENGINE

A system includes a steam turbine. The steam turbine includes an outer casing and an inner casing disposed within the outer casing. The inner casing is horizontally split in an axial direction into an upper inner casing portion and a lower inner casing portion. The steam turbine also includes an impulse stage disposed within the inner casing, wherein the inner casing is configured to provide full arc admission of a fluid to the impulse stage. The steam turbine further includes at least one reaction stage having multiple blades. The at least one reaction stage is integrated within the inner casing. 1. A system , comprising: an outer casing; and', 'an inner casing disposed within the outer casing, wherein the inner casing is horizontally split in an axial direction into an upper inner casing portion and a lower inner casing portion;', 'an impulse stage disposed within the inner casing, wherein the inner casing is configured to provide full arc admission of a fluid to the impulse stage;', 'at least one reaction stage comprising a plurality of blades, wherein the at least one reaction stage is integrated within the inner casing., 'a steam turbine comprising2. The system of claim 1 , wherein the impulse stage is disposed within the inner casing upstream of the at least one reaction stage.3. The system of claim 1 , wherein the inner casing comprises a plurality of steam ducts that define a fluid flow path through the upper and lower inner casing portions claim 1 , and the fluid flow path is configured to provide full arc admission of the fluid to the impulse stage via the fluid flow path.4. The system of claim 3 , wherein the inner casing comprises a flange horizontally split in the axial direction claim 3 , the upper inner casing portion comprises an upper flange portion and the lower inner casing portion comprises a lower flange portion claim 3 , and the upper and lower flange portions form the flange.5. The system of claim 4 , wherein the at least one steam duct of the ...

TURBO-ENGINE HOUSING, EQUIPPED WITH A THERMAL PROTECTION SHELL AND AN ANTI-WEAR STRIP

A turbo-engine module comprises a turbo-engine housing, and a thermal protection shell of the housing. The thermal protection shell is configured to cover at least partially the housing in order to protect same thermally. The module comprises a wear protection strip which is situated between the housing and the thermal protection shell, in a junction region of the housing and the thermal protection shell. 1. A turbo-engine module , comprising:a turbo-engine housing,a thermal protection shell of the housing, wherein the thermal protection shell is configured to cover at least partially the housing in order to protect the housing thermally,wherein the module comprises a wear protection strip which is situated between the housing and the thermal protection shell in a junction region of the housing and the thermal protection shell,wherein the wear protection strip comprises at least one recess, wherein the wear protection strip is open-worked at the recess,wherein the recess is situated outside a zone for fastening the wear protection strip to the thermal protection shell and/or wherein the recess is situated outside a zone for fastening the wear protection strip to the housing.2. The turbo-engine module according to claim 1 , wherein the wear protection strip covers a housing portion claim 1 , wherein the wear protection strip is made of the same material as the material of the housing portion claim 1 , and/or wherein the wear protection strip is made of the same material as the material of the thermal protection shell.3. The turbo-engine module according to claim 1 , wherein the wear protection strip has a thickness between 0.3 mm and 0.8 mm.4. The turbo-engine module according to claim 1 , wherein the thermal protection shell is secured to the housing by at least one attachment claim 1 ,wherein the wear protection strip is fastened to the housing and to the thermal protection shell by the attachment.5. The turbo-engine module according to claim 4 , wherein the ...

STEAM TURBINE AND METHOD FOR OPERATING SAME

A steam turbine, having a steam turbine outer housing; a high-pressure inner housing having first process steam inlet and outlet sections for conducting process steam therethrough from the inlet to the outlet section in a first process steam expansion direction; a low-pressure inner housing having second process steam inlet and outlet sections for conducting process steam therethrough from the second process steam inlet section to the second process steam outlet section in a second process steam expansion direction; and an intermediate superheater, which is arranged downstream of the high-pressure inner housing and upstream of the low-pressure inner housing, wherein the high-pressure and low-pressure inner housings are arranged within the steam turbine outer housing and the high-pressure and the low-pressure inner housings are arranged in such a way that the first steam inlet section of the high-pressure inner housing faces the second steam inlet section of the low-pressure inner housing. 1. A steam turbine , comprising:a steam turbine outer housing,a high-pressure inner housing with a first process steam inlet portion and a first process steam outlet portion for conducting process steam through the high-pressure inner housing from the first process steam inlet portion to the first process steam outlet portion in a first process steam expansion direction,a low-pressure inner housing with a second process steam inlet portion and a second process steam outlet portion for conducting process steam through the low-pressure inner housing from the second process steam inlet portion to the second process steam outlet portion in a second process steam expansion direction, andan intermediate superheater which is arranged downstream of the high-pressure inner housing and upstream of the low-pressure inner housing, wherein the high-pressure inner housing and the low-pressure inner housing are arranged within the steam turbine outer housing,wherein the high-pressure inner ...

TURBINE HOUSING FOR AN EXHAUST GAS TURBOCHARGER

The invention relates to a turbine housing () for an exhaust gas turbocharger. The turbine housing () comprises an outer housing () and an inner housing () as well as a bearing flange (). The outer housing () is joined to the bearing flange (). The inner housing () comprises a first shell component () and a second shell component (), wherein said first shell component and said second shell component are made of different cast steel materials and are placed side by side in a transverse plane (QE), which is oriented transversely to the longitudinal axis (LA) of the turbine housing (), and are joined to each other. The bearing flange () is a one-piece part, made of uniform material, of the first shell component (). 13453547878. Turbine housing , which is designed for an exhaust gas turbocharger and which comprises an outer housing () and an inner housing () as well as a bearing flange () , wherein the outer housing () is joined to the bearing flange () , characterized in that the inner housing () comprises a first shell component () and a second shell component () , said first shell component and said second shell component being joined to each other; and the two shell components ( , ) are made of different cast steel materials.257. Turbine housing claim 1 , as claimed in claim 1 , characterized in that the bearing flange () is a one-piece part claim 1 , made of uniform material claim 1 , of the first shell component ().37821094. Turbine housing claim 1 , as claimed in claim 1 , characterized in that the two shell components ( claim 1 , ) are placed side by side in a transverse plane (QE) claim 1 , which is oriented transversely to the longitudinal axis (LA) of the turbine housing () claim 1 , and are connected to each other by means of a circumferential joint claim 1 , seam () on the outer periphery () of the inner housing ().451335. Turbine housing claim 1 , as claimed in claim 1 , characterized in that the bearing flange () has an external circumferential web () ...

GAS TURBINE ENGINE AND FRAME

One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique frame for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine frames. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. 1. A gas turbine engine frame , comprising:a metallic inner hub;a metallic flange;a metallic outer construction; anda composite flowpath structure comprising a primary flowpath structure disposed between the metallic inner hub and the metallic outer construction, wherein the composite flowpath structure includes at least one of carbon bismaleimide composites, ceramic matrix composites, metal matrix composites, organic matrix composites or carbon-carbon composites, and wherein the metallic flange is configured to secure the composite flowpath structure to the metallic inner hub;wherein the primary flowpath structure comprises a primary composite outer flowpath wall and a primary composite inner flowpath wall spaced radially apart from the primary composite outer flowpath wall, and the primary composite outer flowpath wall and the primary composite inner flowpath wall together define the primary flowpath structure for a working fluid of the gas turbine engine; andwherein the composite flowpath structure further comprises a plurality of inner composite struts, wherein at least a portion of each inner composite strut extends between the primary composite inner flowpath wall and the primary composite outer flowpath wall.2. The gas turbine engine frame of claim 1 , further comprising metallic struts extending between the metallic inner hub and the metallic outer construction claim 1 , wherein the metallic inner hub claim 1 , the metallic struts and the metallic outer construction are assembled to form a loadpath to transfer ...

COOLING ARRANGEMENT FOR A TURBINE CASING OF A GAS TURBINE ENGINE

There is disclosed a cooling arrangement for a turbine casing () of a gas turbine engine (). The cooling arrangement comprises a first cooling duct () that is at least partly within a second cooling duct (). The first cooling duct is for a first cooling fluid flow and the second cooling duct is for a second cooling fluid flow which flows around the first cooling duct. 1. A cooling arrangement for a turbine casing of a gas turbine engine , comprising a first cooling duct that is located within a second cooling duct , wherein the first cooling duct is for a first cooling fluid flow and wherein the second cooling duct is for a second cooling fluid flow which in use flows around the first cooling duct.2. A cooling arrangement as claimed in claim 1 , wherein the first cooling duct and the second cooling duct feed into a single manifold having outlet holes for directing cooling fluid towards the turbine casing.3. A cooling arrangement as claimed in claim 1 , wherein the first cooling duct and the second cooling duct feed into separate manifolds claim 1 , each manifold having outlet holes for directing cooling fluid towards the turbine casing.4. A cooling arrangement as claimed in claim 1 , wherein the first cooling duct is enclosed by the second cooling duct along the majority or substantially all of its length.5. A cooling arrangement as claimed in claim 1 , wherein the second cooling duct is configured to allow the cooling fluid to flow therethrough substantially unmodulated.6. A cooling arrangement as claimed in claim 1 , wherein electronic equipment and/or one or more cables are mounted to the first cooling duct.7. A cooling arrangement as claimed in claim 6 , wherein the electronic equipment and/or the one or more cables are mounted to an inner side and/or an outer side of the first cooling duct.8. A cooling arrangement as claimed in claim 1 , wherein the first cooling duct comprises a valve for controlling the flow of the first cooling fluid.9. A cooling arrangement ...

TURBINE HOUSING

An outer housing formed of a sheet metal is provided such that its open end portion surrounds an outer edge portion of an inner housing formed by casting. An outer protrusion an annular protrusion and a connecting portion are provided on the outer edge portion of the inner housing The open end portion of the outer housing is joined to a protruding end of the outer protrusion a protruding end of the annular protrusion and an end edge of the connecting portion whereby the inner housing and the outer housing are integrated. 1. A turbine housing comprising:an inner housing formed by casting and including a scroll tube portion which surrounds a turbine chamber for accommodating a turbine impeller and has a scroll flow passage through which a flow exhaust gas flows circularly and goes out to the turbine chamber, and an introduction tube portion which leads an inflow exhaust gas to the scroll flow passage, and an outlet passage portion through which the flow exhaust gas flows out of the turbine chamber flows; andan outer housing formed of a sheet metal and including an open end portion which surrounds an outer edge portion of the inner housing when viewed in a direction of a scroll center line and an exhaust outlet which is provided on a side opposite the open end portion and through which the flow exhaust gas flowing out of the outlet passage portion is discharged,wherein the inner housing has a protrusion protruding outward from the outer edge portion of the inner housing, and a protruding end of the protrusion and the open end portion of the outer housing are joined to each other, whereby the outer housing and the inner housing are integrated.2. A turbine housing according to claim 1 , whereinthe scroll flow passage has a flow passage inlet through which the flow exhaust gas flows into the scroll flow passage, and a flow passage outlet through which the flow exhaust gas flows out of the scroll flow passage, and a merging portion in which the flow exhaust gas flowing out ...

FORGED CAST FORGED OUTER CASE FOR A GAS TURBINE ENGINE

A case for a gas turbine engine includes a cast case section cast case section configured to be welded between a forward case section and an aft case section. 1. A case assembly for a gas turbine engine , comprising:a cast case section cast case section configured to be welded between a forward case section and an aft case section.2. The case assembly as recited in claim 1 , wherein said cast case section includes a machined interface.3. The case assembly as recited in claim 1 , wherein said cast case section includes a raised boss.4. The case assembly as recited in claim 1 , wherein said cast case section includes a machined surface.5. The case assembly as recited in claim 1 , wherein said forward case section and said aft case section are forged.6. The case assembly as recited in claim 5 , wherein said forged forward case section is configured for containment of a high pressure turbine rotor stage.7. The case assembly as recited in claim 6 , wherein said forged forward case section includes a forward flange.8. The case assembly as recited in claim 6 , wherein said forged aft case section is configured for containment of a low pressure turbine rotor stage.9. The case assembly as recited in claim 8 , wherein said forged aft case section includes an aft flange.10. The case assembly as recited in claim 5 , wherein said forged forward case section and said forged aft case section define respective forward and aft containment zones.11. The case assembly as recited in claim 1 , wherein said forged forward case section and said forged aft case section define respective forward and aft containment zones.12. The case assembly as recited in claim 1 , further comprising a forward weld between said forged forward case section and said cast case section outside of said forward containment zone and an aft weld between said cast case section and said forged aft case section outside of said aft containment zone.13. The case assembly as recited in claim 1 , wherein said case is a ...

Turbine Assembly Method

A turbine assembly method includes a positional information measurement process in which positional information on a plurality of specific portions set on an outer surface of a casing is measured in a state before releasing of bolt fastening of the casing at a time of disassembly of the turbine and in a predetermined disassembly state after the releasing of the bolt fastening, and an alignment process in which positional adjustment of a stationary component with respect to the casing is made based on the measurement results of the positional information on the specific portions in the positional information measurement process. 1. A method of assembling a turbine including a casing divided into a casing lower part and a casing upper part , a turbine rotor contained in the casing , and a stationary component supported inside the casing and divided into a lower side and an upper side , the casing lower part and the casing upper part being connected together by bolt fastening ,the method comprising:a positional information measurement process in which positional information on a plurality of specific portions set on an outer surface of the casing is measured in a state before releasing of bolt fastening of the casing at a time of disassembly of the turbine and in a predetermined disassembly state after the releasing of the bolt fastening; andan alignment process in which positional adjustment of the stationary component with respect to the casing is made based on measurement results in the positional information measurement process.2. The method of assembling the turbine according to claim 1 , whereinthe predetermined disassembly state after the releasing of the bolt fastening of the casing in the positional information measurement process is a state in which the casing upper part, the upper side of the stationary component, and the turbine rotor are removed, andthe specific portions are set on the casing lower part.3. The method of assembling the turbine according to ...

STEAM TURBINE

A steam turbine according to an embodiment includes an outer casing, an inner casing, a turbine rotor, and a pair of inner casing regulating portions. The pair of inner casing regulating portions regulates movement of the inner casing in a direction orthogonal to an axial direction of the turbine rotor. The pair of inner casing regulating portions is disposed beneath the inner casing at positions different from each other in the axial direction and is supported by a regulating supporting portion extending upward from a bottom portion of the outer casing. 1. A steam turbine configured to discharge steam laterally , the steam turbine comprising:an outer casing;an inner casing housed in the outer casing;a turbine rotor penetrating the inner casing and the outer casing; anda pair of inner casing regulating portions provided inside the outer casing, the pair of inner casing regulating portions being configured to regulate movement of the inner casing in a direction orthogonal to an axial direction of the turbine rotor,wherein the pair of inner casing regulating portions is disposed beneath the inner casing at positions different from each other in the axial direction and is supported by a regulating supporting portion extending upward from a bottom portion of the outer casing.2. The steam turbine according to claim 1 , wherein the regulating supporting portion has a projected area projected on a vertical plane including a shaft center line of the turbine rotor claim 1 , the projected area being smaller than a projected area projected on a vertical plane vertical to the shaft center line.3. The steam turbine according to claim 1 , wherein the regulating supporting portion includes a first vertical supporting beam configured to support one of the inner casing regulating portions claim 1 , and a second vertical supporting beam configured to support the other inner casing regulating portion.4. The steam turbine according to claim 1 , wherein the regulating supporting portion ...

STEAM TURBINE

A steam turbine according to an embodiment includes an outer casing; an inner casing housed in the outer casing; a turbine rotor penetrating the inner casing and the outer casing; and a supporting beam provided inside the outer casing. The supporting beam extends in an axial direction of the turbine rotor and supports the inner casing. The outer casing includes outer casing supporting portions which are provided at both ends of the outer casing in the axial direction and are supported by the foundation. The supporting beam has beam end portions provided at both ends in the axial direction. Each of the outer casing supporting portions includes a supporting surface that supports the corresponding beam end portion. 1. A steam turbine provided on a foundation , the steam turbine comprising:an outer casing;an inner casing housed inside the outer casing;a turbine rotor penetrating the inner casing and the outer casing; anda supporting beam provided inside the outer casing, the supporting beam extending in an axial direction of the turbine rotor and being configured to support the inner casing,wherein the outer casing includes outer casing supporting portions that are provided at both ends of the outer casing in the axial direction and are supported by the foundation, andthe supporting beam includes beam end portions provided at both ends in the axial direction,wherein each of the outer casing supporting portions includes a supporting surface that supports the corresponding beam end portion.2. The steam turbine according to claim 1 , wherein the outer casing includes first end walls facing the corresponding beam end portion in the axial direction claim 1 ,wherein a gap is provided between each of the beam end portions of the supporting beam and the corresponding first end wall.3. The steam turbine according to claim 1 , wherein the outer casing includes a pair of second end walls facing the corresponding beam end portion in a direction orthogonal to the axial direction as ...

INTERSTAGE SEAL HOUSING OPTIMIZATION SYSTEM IN A GAS TURBINE ENGINE

An interstage seal system () for adjusting the position of an interstage seal during operation of a gas turbine engine () to increase efficiency of the seal () is disclosed. The interstage seal system () may include a interstage seal housing () formed from a circumferentially extending housing having a seal () positioned on a radially inward surface () of the interstage seal housing (). The interstage seal housing () may biased radially outward via one or more springs () to bias the radially inward surface () of the interstage seal housing () outwardly. The interstage seal housing () may reside in an interstage housing receiving cavity (). The cavity () may be supplied with gases at a higher pressure than on the other side () of the seal housing () during turbine engine operation. As such, the interstage seal housing () is forced radially inwardly to close the gap () within the seal () as the high pressure force directed radially inward overcomes the spring bias directed radially outward. 1. A system for a radial position of an interstage seal housing within a gas turbine engine , comprising:an interstage seal housing formed from a circumferentially extending housing having a seal positioned on a radially inward surface of the interstage seal housing;at least one biasing support extending radially outward from the interstage seal housing;at least one spring coupled to the at least one biasing support to bias the radially inward surface of the interstage seal housing; andat least one side wave spring extending between an outer surface of the interstage seal housing into contact with an adjacent component of the gas turbine engine.2. The system of claim 1 , wherein the interstage seal housing has an axially extending upstream support arm with a radially inward sealing surface and forming an upstream cavity for receiving a first hook of the interstage seal housing support claim 1 , and has an axially extending downstream support arm with a radially inward sealing ...

CASING COOLING DUCT

A turbine includes an inner casing to which at least a stator vane of a turbine section is mountable, and an outer casing arranged around the inner casing in such a way that an outer cooling channel is formed between the inner casing and the outer casing. The outer cooling channel includes a fluid inlet through which a cooling fluid is injectable from an outer volume of the turbine into the outer cooling channel. The cooling channel includes a fluid outlet such that the cooling fluid is exhausted into an inner volume of the turbine. The fluid inlet is located with respect to the fluid outlet such that the cooling fluid inside the outer cooling channel includes a flow direction which has a component that is orientated in opposite direction with respect to a main flow direction of a working fluid of the turbine. 112-. (canceled)13. A turbine , comprising:an inner casing to which at least a stator vane of a turbine section is mountable, andan outer casing, which is arranged around the inner casing in such a way that an outer cooling channel is formed between the inner casing and the outer casing,wherein the outer cooling channel comprises a fluid inlet through which a cooling fluid is injectable from an outer volume of the turbine into the outer cooling channel,wherein the cooling channel comprises a fluid outlet such that the cooling fluid is exhausted into an inner volume of the turbine,wherein the fluid inlet is located with respect to the fluid outlet such that the cooling fluid inside the outer cooling channel comprises a flow direction which has a component that is orientated in opposite direction with respect to a main flow direction of a working fluid of the turbine.14. The turbine according to claim 13 , wherein the fluid inlet is formed in the outer casing.15. The turbine according to claim 13 , wherein the fluid outlet is formed in the inner casing.16. The turbine according to claim 13 , wherein the outer cooling channel is formed with a converging shape for ...

SEALING SYSTEM FOR TURBINE SHROUD SEGMENTS

A turbine shroud is disposed between stages of stationary turbine nozzles. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface and opposite ends. Each end includes an end face, an end cutback face spaced from the end face, and an intermediate surface extending between the end face and the end cutback face to define a recess. One or more seals overlap the recess of a circumferentially adjacent pair of shroud segments to produce a sealed joint. 1. A turbine engine comprising:a rotor comprising a plurality of stationary nozzles arranged in a first stage and an adjacent second stage; anda shroud disposed between the first stage and the adjacent second stage of the plurality of stationary nozzles, wherein the shroud comprises a plurality of arcuate shroud segments sealingly engaged with one another, the plurality of arcuate shroud segments including a first shroud segment and a second shroud segment circumferentially adjacent the first shroud segment;wherein each arcuate shroud segment of the plurality of arcuate shroud segments comprises a bottom panel, the bottom panel having a radially inner surface, a radially outer surface, a first end, and a second end;wherein the first end comprises a first end face extending radially outward from the radially inner surface of the bottom panel, a first end cutback face circumferentially spaced from the first end face and extending radially inward from the radially outer surface of the bottom panel, and a first intermediate surface extending between the first end face and the first end cutback face to define a first recess;wherein the second end comprises a second end face extending radially outward from the radially inner surface of the bottom panel, a second end cutback face circumferentially spaced from the second end face and extending radially inward from the radially outer surface of the ...

STRESS MITIGATING ARRANGEMENT FOR WORKING FLUID DAM IN TURBINE SYSTEM

A casing half shell for a turbine system, a steam turbine system and related method are provided. The casing half shell includes a body having an open interior for enclosing parts of the turbine system; a first inlet in the body for delivering a first working fluid flow into the open interior in a first direction; and a second inlet in the body for delivering a second working fluid flow into the open interior in a second direction that is opposed to the first direction. A working fluid dam extends radially and axially in the body between the first inlet and the second inlet, the working fluid dam includes a stress-mitigating slot extending radially therein. A fill member may be mounted in the stress-mitigating slot to provide full functioning of the working fluid dam. 1. A casing half shell for a turbine system , the casing half shell comprising:a body having an open interior for enclosing parts of the turbine system;a first working fluid flow path in the body for directing a first working fluid flow in the open interior in a first direction;a second working fluid flow path in the body for directing a second working fluid flow in the open interior in a second direction that is opposed to the first direction; anda working fluid dam extending radially and axially in the body between the first working fluid flow path and the second working fluid flow path, the working fluid dam including a stress-mitigating slot extending radially therein.2. The casing half shell of claim 1 , further comprising a fill member mounted in the stress-mitigating slot.3. The casing half shell of claim 2 , wherein the body further includes a packing head main fit upstream of the working fluid dam and a diaphragm mounting element downstream of the working fluid dam.4. The casing half shell of claim 3 , wherein the stress-mitigating slot extends adjacent an axially facing surface of the packing head main fit claim 3 , and the fill member is fixedly coupled to the packing head main fit.5. The ...

STEAM TURBINE

The steam turbine of an embodiment has: an outer casing; an inner casing housed in the outer casing; a turbine rotor penetrating the inner casing and the outer casing; and a support beam provided in the outer casing, extending in an axial direction of the turbine rotor, and supporting the inner casing, and is disposed on a foundation. The outer casing has outer casing support portions provided in both end portions of the outer casing in the axial direction of the turbine rotor and supported by the foundation. The support beam has beam end portions provided in both end portions in the axial direction of the turbine rotor. The outer casing support portion has a support surface supporting the beam end portion. Further, the outer casing includes a height adjustment mechanism capable of accessing the beam end portion from the outside of the outer casing. 1. A steam turbine disposed on a foundation , the steam turbine comprising:an outer casing;an inner casing housed in the outer casing;a turbine rotor penetrating the inner casing and the outer casing; anda support beam provided in the outer casing, extending in an axial direction of the turbine rotor, and supporting the inner casing, wherein 'outer casing support portions provided in both end portions of the outer casing in the axial direction of the turbine rotor and supported by the foundation,', 'the outer casing comprises 'beam end portions provided in both end portions in the axial direction of the turbine rotor,', 'the support beam comprises 'a support surface supporting the beam end portion, and', 'the outer casing support portion comprisesthe outer casing includes a height adjustment mechanism capable of accessing the beam end portion from the outside of the outer casing.2. The steam turbine according to claim 1 , whereinthe inner casing comprises an arm portion supported by the support beam.3. The steam turbine according to claim 1 , wherein 'a downward exhaust port provided in a lower end portion and ...

Stationary airfoils configured to form improved slip joints in bi-cast turbine engine components and the turbine engine components including the same

Stationary airfoils configured to form an improved slip joint in bi-cast turbine engine components and the turbine engine components including the same are provided. The stationary airfoil for a bi-cast turbine engine component comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. An end portion is shaped with a pair of opposing flanges to form a slip joint with a shroud ring in the bi-cast turbine engine component and to define an interlocking feature. The slip joint permits radial movement of the stationary airfoil relative to the shroud ring due to thermal differential expansion and contraction.

COMPRESSOR DISCHARGE CASING ASSEMBLY

A compressor discharge casing assembly includes a diffuser disposed proximate an aft region of a compressor section, the diffuser configured to route a compressed airflow to an interior region of the compressor discharge casing assembly. Also included is a strut disposed in the interior region of the compressor discharge casing assembly and located proximate an exit region of the diffuser. Further included is a heat shield disposed proximate an upstream portion of the strut, the heat shield configured to reduce impingement of the compressed airflow on the strut. 1. A compressor discharge casing assembly comprising:a diffuser disposed proximate an aft region of a compressor section, the diffuser configured to route a compressed airflow to an interior region of the compressor discharge casing assembly;a strut disposed in the interior region of the compressor discharge casing assembly and located proximate an exit region of the diffuser; anda heat shield disposed proximate an upstream portion of the strut, the heat shield configured to reduce impingement of the compressed airflow on the strut.2. The compressor discharge casing assembly of claim 1 , wherein the strut is operatively coupled to claim 1 , and extends between claim 1 , a compressor discharge casing bulkhead and an inner support ring.3. The compressor discharge casing assembly of claim 1 , wherein the heat shield is operatively coupled to the strut.4. The compressor discharge casing assembly of claim 2 , further comprising a nozzle disposed proximate an inlet of a turbine section claim 2 , the nozzle operatively coupled to the inner support ring and an outer support ring.5. The compressor discharge casing assembly of claim 4 , wherein the heat shield is configured to reduce a rate of thermal growth of the strut.6. The compressor discharge casing assembly of claim 4 , wherein the heat shield is configured to reduce relative motion between a transition piece and the nozzle.7. The compressor discharge casing ...

OUTER DIFFUSER CASE FOR A GAS TURBINE ENGINE

An outer diffuser case of a diffuser case assembly for use in a gas turbine engine may have a housing orientated about an engine axis, a forward flange projecting radially outward from the housing, a mid-flange spaced axially aft of the forward flange and projecting radially inward from the housing, and an aft flange projecting radially outward from the housing. The mid flange is spaced axially between the forward and aft flanges and is configured to detachably engage an inner diffuser case of the case assembly. The forward flange is configured to detachably engage a high pressure compressor and the aft flange is configured to detachably engage a high pressure turbine of the engine. 1. An outer diffuser case for use in a gas turbine engine , the outer diffuser case comprising:a housing orientated about an axis;a forward flange projecting radially outward from the housing and configured to detachably engage a high pressure compressor;an aft flange spaced axially downstream from the forward flange, projecting radially outward from the housing, and configured to detachably engage a high pressure turbine; anda mid-flange spaced axially between the forward and aft flanges and projecting radially inward from the housing, and wherein the mid flange is configured to detachably engage an inner diffuser case.2. The outer diffuser case set forth in claim 1 , wherein the housing is cone shaped and diverges in a downstream direction.3. The outer diffuser case set forth in claim 2 , wherein the housing diverges by about 2.5 degrees.4. The outer diffuser case set forth in claim 1 , wherein the housing has an axial length within a range of about 39.200 to 39.210 cm claim 1 , and an outer diameter proximate to the forward flange within a range of about 51.864 to 51.890 cm.5. The outer diffuser case set forth in claim 4 , wherein the housing has a minimum wall thickness proximate to the aft flange within a range of about 0.305 to 0.330 cm.6. The outer diffuser case set forth in claim ...

ADDITIVE MANUFACTURED CASE WITH INTERNAL PASSAGES FOR ACTIVE CLEARANCE CONTROL

An engine or engine casing having an inner annular case and an outer annular case. The engine casing is formed using an additive manufacturing technique such that the inner annular case and outer annular case is formed surrounding a hollow inner annular cavity. The annular cavity includes a pin bank connecting the inner annular case and outer annular case. The pin bank improves heat transfer between the inner and outer annular case and provide structural support to the inner and outer annular case. By providing fluid flow through the annular cavity, the turbine casing can be cooled and the radius of the casing can be controlled through the regulation of fluid travelling within the annular cavity. By controlling the fluid flow though the annular cavity, the engine case may be cooled to regulate its temperature in a wide variety of operating conditions. Further, the regulation of fluid in the annular cavity allows for active clearance control of the spacing between the turbine blades or vanes and seals used in the turbine. 1. A turbine engine comprising:an annular inner wall surrounding a turbine assembly, the turbine assembly rotating around a first axis;an annular outer wall at least partially surrounding the annular inner wall and forming an annular cavity between the annular inner wall and the annular outer wall;wherein the annular outer wall has at least one upstream opening at an axially forward position on the first axis in fluid communication with the annular cavity and the annular cavity has an outlet at an axially aft position on the first axis allowing fluid to pass from the upstream opening along the annular cavity through the outlet.2. The engine of further comprising a valve connected to at least one of the upstream opening and the outlet for controlling fluid flow in the annular cavity.3. The engine of claim 1 , wherein fluid passes along the annular cavity due to a pressure difference between the upstream opening and the outlet.4. The engine of claim 1 ...